[Federal Register Volume 59, Number 213 (Friday, November 4, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-26879]
[[Page Unknown]]
[Federal Register: November 4, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-SW-10-AD; Amendment 39-9059; AD 94-17-07]
Airworthiness Directives; Robinson Helicopter Company Model R22
Series Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 94-17-07 which was sent
previously to all known U.S. owners and operators of Robinson
Helicopter Company Model R22 series helicopters by individual letters.
This AD requires an inspection and repetitive visual checks for
slippage of the tail rotor (T/R) drive and replacement of the T/R
gearbox, if necessary. This amendment is prompted by two incidents in
which the T/R output key (key) was not installed between the output
shaft and the output pinion during assembly of the T/R gearbox. The
actions specified by this AD are intended to prevent slippage of the T/
R drive, loss of directional control, and subsequent loss of control of
the helicopter.
DATES: Effective on November 21, 1994, to all persons except those
persons to whom it was made immediately effective by Priority Letter AD
94-17-07, issued on August 25, 1994, which contained the requirements
of this amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 21,1994.
Comments for inclusion in the Rules Docket must be received on or
before January 3, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 94-SW-10-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
The applicable service information may be obtained from Robinson
Helicopter Company, 24747 Crenshaw Blvd., Torrance, CA 90505. This
information may be examined at the FAA, Office of the Assistant Chief
Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the
Office of the Federal Register, 800 North Capitol Street NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Ms. Elizabeth Bumann, Aerospace
Engineer, Los Angeles Aircraft Certification Office, Propulsion Branch,
FAA, 3229 E. Spring Street, Long Beach, California 90806-2425,
telephone (310) 988-5265, fax (310) 988-5210.
SUPPLEMENTARY INFORMATION: On August 25, 1994, the FAA issued Priority
Letter AD 94-17-07, applicable to Robinson Helicopter Company R22
series helicopters, which requires an inspection and repetitive visual
checks for slippage of the tail rotor (T/R) drive, and replacement of
the T/R gearbox, if necessary. That action was prompted by two
incidents in which the T/R output key (key) was not installed between
the output shaft and the output pinion during assembly of the T/R
gearbox. The key is required to prevent the output gear from rotating
on the output shaft. Both incidents resulted in slippage of the T/R
drive. On June 2, 1994, Registro Aeronautico Italiano (RAI), the
Airworthiness Authority of Italy, issued RAI AD No. 94-131 to require a
daily inspection to determine if there had been any slippage of the T/R
drive between the output shaft and the output pinion. This condition,
if not corrected, could result in slippage of the T/R drive, loss of
directional control, and subsequent loss of control of the helicopter.
The FAA has reviewed Robinson Helicopter Company R22 Service
Bulletin (SB) #74, dated July 18, 1994, that describes procedures for
determining slippage of the T/R drive using a 35-lb. load on the T/R
blade and checking for correct alignment of dots that have been marked
in accordance with SB #74, dated July 18, 1994. The FAA is issuing this
AD to require the initial marking of dots and an inspection prior to
further flight, rather than within the next 20 hours time-in-service
(TIS) as specified by SB #74, dated July 18, 1994.
Since the unsafe condition described is likely to exist or develop
on other Robinson Helicopter Company Model R22 series helicopters of
the same type design, the FAA issued Priority Letter AD 94-17-07 to
prevent slippage of the T/R drive, loss of directional control, and
subsequent loss of control of the helicopter. The AD requires the
installation of alignment marks, an initial inspection prior to further
flight, daily pre-flight visual checks for slippage of the T/R drive,
and replacement of the T/R gearbox, if necessary. The actions are
required to be accomplished in accordance with the service bulletin
described previously. This AD is considered to be an interim action.
The FAA is considering further rulemaking to require opening the T/R
gearbox and verifying installation of the key as the terminating action
to this AD.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on August 25, 1994, to all known U.S. owners and operators of
Robinson Helicopter Company Model R22 series helicopters. These
conditions still exist, and the AD is hereby published in the Federal
Register as an amendment to section 39.13 of the Federal Aviation
Regulations (14 CFR 39.13) to make it effective to all persons.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 94-SW-10-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
to read as follows:
AD 94-17-07 Robinson Helicopter Company: Amendment 39-9059. Docket
No. 94-SW-10-AD.
Applicability: Model R22 series helicopters, certificated in any
category with tail rotor (T/R) gearboxes that were manufactured or
overhauled by Robinson Helicopter Company prior to June 8, 1992. The
following gearbox S/N's have been determined to have the T/R output
key (key) installed and are therefore exempt from this AD: 0012,
0013, 0014, 0020, 0021, 0040, 0054, 0062, 0091, 0095, 0098, 0108,
0121, 0134, 0137, 0153, 0169, 0179, 0185, 0191, 0201, 0205, 0227,
0228, 0235, 0248, 0258, 0262, 0272, 0277, 0280, 0321, 0333, 0342,
0365, 0432, 0439, 0444, 0503, 0504, 0525, 0548, 0558, 0559, 0565,
0574, 0576, 0592, 0594, 0597, 0603, 0604, 0605, 0615, 0632, 0641,
0644, 0650, 0656, 0662, 0663, 0674, 0686, 0689, 0696, 0697, 0700,
0702, 0707, 0722, 0734, 0735, 0736, 0742, 0759, 0767, 0777, 0778,
0805, 0832, 0836, 0839, 0842, 0850, 0862, 0866, 0868, 0887, 0892,
0937, 0939, 0983, 0986, 0996, 0998, 1018, 1021, 1029, 1030, 1035,
1072, 1081, 1087, 1104, 1116, 1121, 1126, 1129, 1132, 1141, 1151,
1176, 1186, 1187, 1199, 1205, 1208, 1217, 1222, 1228, 1233, 1245,
1249, 1269, 1274, 1290, 1293, 1299, 1301, 1307, 1311, 1323, 1330,
1333, 1339, 1341, 1350, 1361, 1379, 1385, 1388, 1392, 1404, 1412,
1428, 1438, 1442, 1450, 1460, 1468, 1494, 1499, 1505, 1509, 1512,
1514, 1526, 1541, 1544, 1578, 1586, 1593, 1595, 1597, 1605, 1610,
1627, 1628, 1636, 1643, 1647, 1648, 1652, 1654, 1686, 1687, 1698,
1701, 1702, 1706, 1710, 1724, 1731, 1732, 1738, 1741, 1750, 1752,
1757, 1759, 1769, 1783, 1800, 1803, 1808, 1814, 1816, 1830, 1844,
1846, 1851, 1852, 1861, 1868, 1871, 1886, 1889, 1901, 1911, 1912,
1927, 1928, 1948, 1959, 1961, 1963, 1965, 1992, 2025, 2034, 2037,
2051, 2071, 2100, 2101, 2103, 2126, 2129, 2136, 2160, 2166, 2170,
2180, 2193, 2203, 2242, 2254, 2265, 2269, 2272, 2279, 2280, 2283,
2294, 2298, 2299, 2304, 2314, 2357, 2377, 2380, 2381, 2395, 2406,
2420, 2421, 2422, 2423, 2425, 2431, 2435, 2436, 2459, 2479, 2492,
2498, 2531, 2539, 2574, 2579, 2582, 2587, 2627, 2634, 2672, 2683,
2697, 2716, 2719, 2721, 2731, 2797, 2863, 2937, 2945.
Compliance: Required as indicated, unless accomplished
previously.
To prevent slippage of the T/R drive, loss of directional
control, and subsequent loss of control of the helicopter,
accomplish the following:
(a) Before further flight, install the alignment dots and
perform an inspection in accordance with Part A of Robinson
Helicopter Company R22 Service Bulletin (SB) #74, dated July 18,
1994. Apply the 35-lb. weight very gently to avoid overstressing the
T/R blade or T/R drive. Any slippage detected must be reported
within 10 days after the inspection to the Manager, Los Angeles
Manufacturing Inspection District Office, FAA, Northwest Mountain
Region, 3229 E. Spring St., Long Beach, California 90806-2425,
telephone (310) 988-5290, fax (310) 988-5293. Reporting requirements
have been approved by the Office of Management and Budget and
assigned OMB control number 2120-0056.
(b) Before the first flight of each day, check for misalignment
of the alignment dots installed on the tail cone skin and the drive
shaft flange by rotating the T/R blade so that the alignment dot is
visible in the inspection window and the tip of the T/R blade
leading edge aligns with the dot on the tail cone skin. Next, ensure
that the drive shaft flange dot is aligned with the dot on the
centerline of the tail cone skin at the edge of the inspection
window. If any misalignment is detected, before further flight,
conduct the inspection required by paragraph (a) of this AD. The
checks required by this AD may be performed by an owner/operator
holding at least a private pilot certificate, and must be entered
into the aircraft records showing compliance with this AD, in
accordance with section 43.11 and 91.417(a)(2)(v) of the Federal
Aviation Regulations.
(c) Verification of the presence of the key through disassembly
and reassembly of the T/R gearbox in accordance with FAA-approved
procedures constitutes terminating action for the requirements of
this AD.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, Los Angeles Aircraft
Certification Office, FAA. Operators shall submit their requests
through an FAA Principal Maintenance Inspector, who may concur or
comment and then send it to the Manager, Los Angeles Aircraft
Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Manager, Los Angeles Aircraft Certification
Office.
(e) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the helicopter to a location where
the requirements of this AD can be accomplished.
(f) The installation, inspection, and checks shall be done in
accordance with Robinson Helicopter Company R22 Service Bulletin
#74, dated July 18, 1994. This incorporation by reference was
approved by the Director of the Federal Register in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
Robinson Helicopter Company, 24747 Crenshaw Blvd. Torrance, CA
90505. Copies may be inspected at the FAA, Office of the Assistant
Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or
at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
(g) This amendment becomes effective on November 21, 1994, to
all persons except those persons to whom it was made immediately
effective by Priority Letter AD 94-17-07, issued August 25, 1994,
which contained the requirements of this amendment.
Issued in Fort Worth, Texas, on October 24, 1994.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 94-26879 Filed 11-3-94; 8:45 am]
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