[Federal Register Volume 60, Number 114 (Wednesday, June 14, 1995)]
[Rules and Regulations]
[Pages 31236-31240]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-14445]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-SW-27-AD; Amendment 39-9276; AD 95-06-03]
Airworthiness Directives; Robinson Helicopter Company Model R22
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) 95-06-03 which was sent
previously to all known U.S. owners and operators of Robinson
Helicopter Company (Robinson) Model R22 helicopters by individual
letters. This AD requires an inspection and modification of the main
rotor (M/R) gearbox. This amendment is prompted by a report of an
incident involving a Model R22 helicopter in which the two M/R mast
spanner nuts (nuts) became loose, resulting in failure of the M/R mast
support structure. The actions specified by this AD are intended to
prevent M/R separation and subsequent loss of control of the
helicopter.
DATES: Effective on June 29, 1995, to all persons except those persons
to whom it was made immediately effective by priority letter AD 95-06-
03, issued on March 8, 1995, which contained the requirements of this
amendment.
Comments for inclusion in the Rules Docket must be received on or
before August 14, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 94-SW-27-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
FOR FURTHER INFORMATION CONTACT: Ms. Elizabeth Bumann, Aerospace
Engineer, FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Blvd., Lakewood, California 90712, telephone (310) 627-5265,
fax (310) 627-5210.
SUPPLEMENTARY INFORMATION: On March 8, 1995, the FAA issued priority
letter AD 95-06-03, applicable to Robinson R22 helicopters, which
requires, within 25 hours time-in-service (TIS) after the effective
date of this AD, removal and disassembly of the M/R gearbox;
measurement of the break-loose torque value of the upper spanner nut;
replacement of the lock washers; increasing the torque values of the
two spanner nuts; reassembly and reinstallation of the M/R gearbox; and
verification of the M/R balance in accordance with the applicable
maintenance manual. That action was prompted by an incident reported by
the Civil Aviation Authority (CAA) of New Zealand involving failure of
the main rotor (M/R) mast support structure. An investigation revealed
that the two M/R mast spanner nuts (nuts) became loose and allowed the
M/R shaft to pull through the retention bearing in the
M/R gearbox. As the loads transferred from the M/R gearbox bearing to
the top of the mast, the rivets that attach the mast bearing outer
housing to the M/R shaft sheared, resulting in failure of the M/R mast
support structure.
Prior to June 15, 1992, the M/R gearbox assembly, P/N A006-1
Revisions A through Z, may have been assembled with paint on the
clamping surface of the M/R shaft, preventing a good clamping surface
for the nuts. Two earlier incidents in Australia prompted the
Commonwealth of Australia CAA to issue CAA AD/R22/35, dated September
1992, to inspect the nuts for looseness and increase the nut torque
values. The FAA did not issue an AD at that time due to inconclusive
information from the two isolated incidents. The compliance procedure
of this AD differs from CAA AD/R22/35 by requiring replacement of the
lock washer, part number (P/N) A269-1, located between the mast bearing
and the upper nut, with a different lock washer, P/N A269-2. The torque
values on both nuts have also been increased. The FAA has determined
that under-torqued nuts may become loose and create an unsafe
condition. Due to the criticality of ensuring that the nuts are
properly torqued, this AD is being issued immediately to correct an
unsafe condition. That condition, if not corrected, could result in M/R
separation and subsequent loss of control of the helicopter.
Since the unsafe condition described is likely to exist or develop
on other Robinson Model R22 helicopters of the same type design, the
FAA issued priority letter AD 95-06-03 to prevent M/R separation and
subsequent loss of control of the helicopter. The AD requires, within
25 hours time-in-service (TIS), removal and disassembly of the M/R
gearbox; measurement of the break-loose torque value of the upper
spanner nut; replacement of the lock washers; increasing the torque
values of the two spanner nuts; reassembly and reinstallation of the M/
R gearbox; and verification of the M/R balance in accordance with the
applicable maintenance manual.
Since the issuance of that AD, the FAA has received information
that Robinson Helicopter Company may not
[[Page 31237]]
be providing to all individuals the MT-124 tool required to remove and
install the nuts. The relevant AD Note has been revised to state that
individuals may request an alternative method of compliance to use a
different nut socket in lieu of the MT-124 tool. Also, Note 1 has been
added to the AD clarifying the applicability to helicopters that have
been modified, altered, or repaired in the area subject to the
requirements of this AD. The addition of this note changed the
numbering of the subsequent notes. Paragraph (a) of the AD has also
been changed to allow use of an unserviceable M/R hub bolt or \5/8\-
inch diameter bolt to counteract torque when removing the nuts.
Finally, nomenclature and part numbers have been added throughout the
AD for clarification. The FAA has determined that these minor changes
will neither change the meaning or scope of the AD nor increase any
burden on any operator.
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 March 8, 1995, to all known U.S. owners and operators of
Robinson Model R22 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-27-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, 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:
95-06-03 Robinson Helicopter Company:
Amendment 39-9276. Docket No. 94-SW-27-AD.
Applicability: Model R22 helicopters with main rotor gearbox
(gearbox), part number (P/N) A006-1, Revisions A through Z,
manufactured or overhauled prior to June 15, 1992, installed,
certificated in any category.
Note 1: This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must use the authority
provided in paragraph (b) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Note 2: The revision level (revision letter) of the gearbox can
be found on the data plate next to the sight glass.
Compliance: Required as indicated, unless accomplished
previously. To prevent main rotor (M/R) separation and subsequent
loss of control of the helicopter, accomplish the following:
(a) Within 25 hours time-in-service after the effective date of
this AD, inspect and modify the gearbox in accordance with the
following:
(1) Remove the gearbox in accordance with the applicable
maintenance manual.
(2) Drain the gearbox by removing the chip detector housing.
(3) Perform the following inspection and torquing of the shaft
retaining nuts.
Note 3: A special tool, a spanner nut socket, P/N MT124-1, may
be obtained from Robinson Helicopter Company. If that tool is not
available, individuals may propose using a different nut socket in
accordance with paragraph (b) of this AD.
(i) Lay the gearbox on its side using care to prevent damage to
the slider tube. Remove the eight NAS1291-4 nuts and two MS20074-04-
10 hex head cap screws holding the sump in place.
(ii) Gently remove the sump and discard the O-ring, using care
to keep all washer-shims on their respective bolts. With the bolts
still attached to the sump, replace the sump nuts on the bolts to
retain the washer-shims (the washer-shim stack is the same at each
location). Hand-tighten the nuts.
(iii) Bend back the two lock washer tabs locking the lower nut,
P/N A153-1. Insert an
[[Page 31238]]
unserviceable M/R hub bolt or a \5/8\-inch diameter bolt through the
teeter hinge bolt hole in the M/R shaft to counteract torque. Clamp
the unserviceable M/R hub bolt or the \5/8\-inch diameter bolt in a
vise or otherwise fasten it to a workbench. Do not clamp the M/R
shaft. Remove the lower nut from the
M/R shaft using a socket, P/N MT124-1, or an FAA-approved equivalent
tool. Remove and discard the lower lock washer, P/N A269-1.
(iv) Bend back the two lock washer tabs locking the upper nut,
P/N A153-1. Remove the upper nut, measuring the torque required to
break the nut loose. Remove and discard the upper lock washer, P/N
A269-1.
(v) If the upper nut required more than 10 ft.-lb. torque to
break loose, proceed to paragraph (a)(3)(vi). If the upper nut
required 10 ft.-lb. torque or less to break loose, report within 5
days the M/R gearbox P/N and break-loose torque value to the
Propulsion Manager, Los Angeles Aircraft Certification Office, 3960
Paramount Blvd., Lakewood, California 90712. Reporting requirements
have been approved by the Office of Management and Budget and
assigned OMB control number 2120-0056. Remove the gear carrier from
the M/R shaft. Inspect the splines and clamping surfaces on both the
shaft and gear carrier for pitting, galling, or scoring of surfaces.
Replace any unairworthy parts. If the inspection revealed no
pitting, galling, or scoring of surfaces, remove any paint from the
clamping surface on the shaft using either paint remover or a
plastic or wooden scraper, and ensure the surface is smooth and
clean. Reassemble the gear carrier to the shaft.
(vi) Inspect the two dowels or roll pins in the gear carrier for
damaged surfaces. Dowels or roll pins must protrude 0.045 to 0.055
inches for proper engagement with the lock washer, P/N A269-2. Also
clean the nuts, M/R shaft threads, and sump, using methyl-ethyl-
ketone (MEK) or Trichlorethane (1,1,1, TCE) before reassembly.
(vii) Install a lock washer, P/N A269-2. Apply anti-seize
(Loctite Anti-seize 767), P/N A257-9, to the M/R shaft threads and
to the chamfered-side face and threads of one nut and install the
nut with the chamfered side against the lock washer. Verify that the
dowels or roll pins are aligned with the holes in the lock washer.
Torque the nut to between 170 and 200 ft.-lb., as required to align
two lock washer tabs (tabs) with the nut. Do not untorque the nut to
align the lock washer tabs with the nut. For the two tabs that are
aligned with the recessed areas, bend down the tabs into the
recessed areas of the nut and inspect the edges of the bent tabs for
cracks.
(viii) Before installing the lock washer,
P/N A269-1, note that the edges are sharp on one side and rounded on
the other. De-burr the sharp edges on two opposite tabs (see figure
1). This will reduce the chance of cracking when these tabs are bent
up. Install the lock washer with the rounded edges toward the
installed nut.
(ix) Apply anti-seize, P/N A257-9, to the chamfered-side face
and threads of the lower nut. Align the two de-burred tabs with the
upper nut and install the lower nut with the chamfered side against
the lock washer. Hand-tighten the nut to hold the washer in place.
Bend the two de-burred tabs up to lock with the upper nut. Torque
the lower nut to between 90 and 120 ft.-lb., as required to align
the two additional tabs. Do not untorque the nut to align the lock
washer tabs with the nut. For the two tabs that are aligned with the
recessed areas, bend down the tabs into the recessed areas of the
nut to lock the lower nut.
(x) Verify that all six bent tabs properly engage the nuts (four
tabs to the upper nut and two to the lower nut), and inspect the
edges of the bent tabs for cracks. Replace any cracked lock washers.
Remove excess anti-seize compound.
(xi) Lubricate the O-ring, P/N A215-271, with oil, P/N A257-2,
and install the O-ring on the sump. Clean and inspect the sealing
surface of the gearbox housing for smoothness. Lightly lubricate the
sealing surface with oil, P/N A257-2.
(xii) Reinstall the sump onto the gearbox housing using the same
washer-shim stacks that were removed in accordance with paragraph
(a)(3)(ii) of this AD. Torque the sump bolts and chip detector as
follows:
(A) For the eight NAS1291-4 nuts on the AN4 bolts for the sump:
90 in.-lb. of torque (includes nut self-locking torque);
(B) For the two cap screws, P/N MS20074: 60 in.-lb. of torque
and install safety wire;
(C) For the chip detector, P/N A7260, (large nut): 150 in.-lb.
of torque and install safety wire;
(D) For the chip detector, P/N A7260, (small nut): 75 in.-lb. of
torque and install safety wire.
Note 4: Be sure to install ground wires under the nut located
aft of the forward right-hand mount.
(4) Reinstall the gearbox in accordance with the applicable
maintenance manual.
(5) Fill the gearbox with oil, P/N A257-2, to the middle of the
sight glass.
(6) Verify the M/R balance in accordance with the applicable
maintenance manual.
(b) 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 5: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles Aircraft Certification Office.
(c) 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.
(d) This amendment becomes effective on June 29, 1995, to all
persons except those persons to whom it was made immediately
effective by Priority Letter AD 95-06-03, issued March 8, 1995,
which contained the requirements of this amendment.
BILLING CODE 4910-13-P
[[Page 31239]]
[GRAPHIC][TIFF OMITTED]TR14JN95.000
BILLING CODE 4910-13-C
[[Page 31240]]
Issued in Fort Worth, Texas, on June 7, 1995.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-14445 Filed 6-13-95; 8:45 am]
BILLING CODE 4910-13-P
