[Federal Register Volume 80, Number 50 (Monday, March 16, 2015)]
[Rules and Regulations]
[Pages 13486-13491]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-05035]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0561; Directorate Identifier 2007-NM-223-AD;
Amendment 39-18111; AD 2015-05-01]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 757-200, -200PF, -200CB, and -300 series
airplanes; and Model 767-200, -300, -300F, and -400ER series airplanes.
This AD was prompted by reports indicating that the counterweights in
some hub assemblies of the ram air turbine (RAT) could be understrength
and fracture when the RAT is rotating, and that some RAT hub assemblies
were delivered with balance washer retention screws that were
incorrectly heat-treated, and therefore, susceptible to fracture and
cracking. This AD requires a part number and serial number inspection
to determine if certain RAT hub assemblies are installed; and, for
affected RAT hub assemblies, doing an inspection for missing and
fractured balance washer screws, and replacement or rework if
necessary. We are issuing this AD to prevent an inoperative RAT, which,
following a dual engine shutdown in flight, will cause loss of all
hydraulic power to the primary flight controls, resulting in subsequent
loss of control of the airplane.
DATES: This AD is effective April 20, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 20,
2015.
ADDRESSES: For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; email
[email protected]; Internet https://www.myboeingfleet.com. For
Hamilton Sundstrand service information identified in this AD, contact
Hamilton Sundstrand, Technical Publications, Mail Stop 302-9, 4747
Harrison Avenue, P.O. Box 7002, Rockford, IL 61125-7002; phone: 860-
654-3575; fax: 860-998-4564; email: [email protected];
Internet: http://www.hamiltonsundstrand.com. You may view this
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call 425-227-1221. It is also
available on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2008-0561.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2008-
0561; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Douglas Tsuji, Senior Aerospace
Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
telephone: 425-917-6546; fax: 425-917-6590; [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to all The Boeing
Company Model 757-200, -200PF, -200CB, and -300 series airplanes; and
Model 767-200, -300, -300F, and -400ER series airplanes. The SNPRM
published in the Federal Register on April 24, 2014 (79 FR 22777). We
preceded the SNPRM with a notice of proposed rulemaking (NPRM) that
published in the Federal Register on May 20, 2008 (73 FR 29087). The
NPRM proposed to require doing an inspection to determine the part
number and serial number of the RAT hub assembly, and replacing the RAT
hub assembly with a new, serviceable, or reworked and re-identified RAT
hub assembly if necessary. The NPRM was prompted by reports indicating
that the counterweights in some hub assemblies of the RATs could be
understrength and fracture when the RAT is rotating. The
[[Page 13487]]
SNPRM proposed to add airplanes to the applicability; add an additional
part number and serial number inspection to determine if certain RAT
hub assemblies are installed; and, for affected RAT hub assemblies,
doing an inspection for missing and fractured balance washer screws,
and replacement if necessary to address an additional defect identified
within the RAT hub assembly. We are issuing this AD to prevent an
inoperative RAT, which, following a dual engine shutdown in flight,
will cause loss of all hydraulic power to the primary flight controls,
resulting in subsequent loss of control of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM (79
FR 22777, April 24, 2014) and the FAA's response to each comment.
Request To Perform a Records Review in Lieu of an Inspection
FedEx requested an option to perform a records review in lieu of an
inspection to determine if any suspect RAT hub assemblies are
installed. FedEx stated that this is to prevent unnecessary inspections
on future Model 767 airplanes delivered from Boeing.
We agree with the commenter's request. The serial number
applicability relates to a sub-assembly of the RAT (the turbine hub
assembly serial number, and not the RAT serial number). Consequently,
many operators might not have such detailed records. However, if an
operator has records indicating the serial number of the turbine hub
assembly that is currently installed on the RAT of a particular
airplane, there is no need to deploy the RAT for inspection to
determine if this AD is applicable. Therefore, a review of airplane
maintenance records is acceptable in lieu of this inspection if the
part number and serial number of the RAT hub assembly can be
conclusively determined from that review. We have revised paragraphs
(g) and (h) of this AD accordingly.
Request for Additional Removal Options (Screw Replacement Information)
United Airlines (UAL) requested that the SNPRM (79 FR 22777, April
24, 2014) be updated to include an additional scenario in which an
operator finds all balance washers in place, but one or more screws
fractured. UAL stated that paragraph 2.B.(5)(d) of Hamilton Sundstrand
Service Bulletin 730814-29-15, dated February 10, 2010 (for Model 757
airplanes); and paragraph 2.B.(5)(d) of Hamilton Sundstrand Service
Bulletin 729548-29-18, dated February 10, 2010 (for Model 767
airplanes); provide on-wing (or off-wing) procedures for the situation
where all balance washers are present, but one or more screws are
fractured. UAL stated that the operator has the option to remove the
screw shank still in the hole with vice grips or a screw extractor in
lieu of RAT or RAT hub replacement.
We disagree with the commenter's request to not replace the RAT or
RAT hub assembly if all washers are in place, but one or more screws
are found fractured during the inspection required by paragraph (h)(1)
of this AD. In this scenario, since any fractured screw is found, the
RAT or RAT hub assembly needs to be replaced with a new, serviceable,
reworked, and re-identified RAT or RAT hub assembly.
Multiple balance washers (of different weights) could be installed
in a location; therefore, depending on how the screw fractures, it may
be possible to lose one, but not all, balance washers. However, it is
most likely that the screw head and all balance washer(s) for that
location will be missing.
However, it is also possible that a screw could fracture during its
removal (i.e., the screw was not found fractured during the inspection
required by paragraph (h)(1) of this AD). This scenario has been
reported on numerous occasions. In this case, it is not necessary to
remove the RAT hub assembly (or RAT) if removal of the fractured screw
is successful (i.e., successful removal of a screw that fractures
during its removal).
The preamble of the SNPRM (79 FR 22777, April 24, 2014) included
the paragraph, ``Screw Replacement Information,'' to provide additional
clarification that if a screw fractures during any screw replacement
and the weight is still available, the balance weight can be installed
with the replacement screw. We further emphasize that screws should
only be replaced one at a time to prevent any potential for a removed
balance washer to be installed in a different location.
We also provide the following additional information. The attempted
removal of a fractured screw can be done without replacement of the RAT
or RAT hub assembly only if the screw fractures during removal, and if
all balance washers originally installed at that location can be
positively accounted for and can be assembled back into that location.
We also note that there could be more than one washer installed at each
location. We have not changed this final rule in this regard.
Request To Not Require Returning Screws to Hamilton Sundstrand
UAL requested the procedure to return all screws or remnants of
fractured screws to Hamilton Sundstrand for further investigation, as
specified in paragraph 2.E., ``Return Balance Washer Screws to Hamilton
Sundstrand,'' of Hamilton Sundstrand Service Bulletin 730814-29-15,
dated February 10, 2010 (for Model 757 airplanes); and in Hamilton
Sundstrand Service Bulletin 729548-29-18, dated February 10, 2010 (for
Model 767 airplanes); not be required. UAL stated that this is an
unnecessary requirement and will only burden the maintenance personnel
with additional logistical procedures that do not add value. UAL also
stated that the balance screw failure issue and root cause are well
understood by Hamilton Sundstrand and that returning failed screws will
not provide additional information.
We agree with the commenter's request. Returning the screws or
fractured screws is not required since the issue is now well
understood. We have added new paragraph (h)(2)(iii) to this AD to
specifically exclude this requirement.
Request To Add New Paragraph To Clarify Compliance for Airplanes in
Production
Boeing requested that a new paragraph be added to paragraph (i) of
the proposed AD (79 FR 22777, April 24, 2014), to read, ``New OEM RAT
hub assemblies not listed in (i)(1) or (i)(2) installed prior to
airplane delivery meet the requirements of paragraph (i). After
delivery, airline operators are responsible for maintaining paragraph
(i) compliance.'' Boeing stated that this language clarifies compliance
for Model 767 airplanes in production.
We partially agree. We do not agree with the commenter's request to
add a new paragraph. However, we agree that clarification is necessary.
For airplanes on which new OEM RAT hub assemblies not listed in
paragraphs (i)(1) and (i)(2) of this AD are installed during
production, it is possible for suspect hub assemblies to be installed,
i.e., a suspect hub assembly might be removed from one airplane and
installed on another airplane. Therefore, an airplane delivered with
conforming parts may no longer have conforming parts due to the
interchangeability of parts in service. All airplanes must comply with
the requirements of paragraph (i) of this AD. We have not changed this
AD in this regard.
[[Page 13488]]
Request To Revise Paragraph (i) of the Proposed AD (79 FR 22777, April
24, 2014)
Boeing requested that paragraph (i)(3) of the proposed AD (79 FR
22777, April 24, 2014) be revised to read as follows: ``As of the
effective date of this AD, no person may install a balance washer screw
having part number (P/N) MS24667-14, on the RAT hub assembly of any
airplane unless a records review can positively determine that the
screws did not come from Northeast Fasteners, lots 24057 and 30533.''
Boeing stated that this language would clarify that the P/N MS24667-14
screw is prohibited only for installation on RAT hub assemblies.
We agree with the commenter's request. Screws having P/N MS24667-14
should not be installed on the RAT hub assembly unless operators can
guarantee the screws did not come from Northeast Fasteners, lots 24057
and 30533. Hamilton Sundstrand was the only company to receive screws
from lot 30533, so no other inventory should be contaminated with them.
Several organizations received screws from lot 24057. All customers who
received the defective screws have been advised of the non-conformance
in lot 24057. There was also a government-industry data exchange
program alert issued to notify other organizations of the potential for
the inventories to be contaminated.
We have determined that balance washer screws with P/N MS24667-14
from Northeast Fasteners, lots 24057 and 30533, are non-conforming and
are unacceptable for use on the RAT hub assembly. The unsafe condition
of this AD is applicable to RAT balance washer screws; therefore, it is
appropriate to limit the required actions to balance washer screws
installed on RAT hub assemblies. We have changed paragraph (i)(3) of
this AD accordingly.
Request for Clarification of Previous Actions
FedEx requested clarification concerning whether credit is given
for accomplishment of previous actions using Boeing Alert Service
Bulletin 757-29A0066, dated January 2, 2007 (for Model 757-200 and -
200PF series airplanes). FedEx stated that it has issued engineering
orders to inspect and replace the RAT hub assemblies, if required, for
possible fractured hub assembly counterweights using Boeing Alert
Service Bulletin 757-29A0066, dated January 2, 2007.
We agree to provide clarification. Paragraph (k) of this AD
provides credit for the actions required by paragraph (g) of this AD,
if those actions were performed before the effective date of this AD
using the service information specified in Boeing Alert Service
Bulletin 757-29A0066, dated January 2, 2007 (for Model 757-200 and -
200PF series airplanes). Boeing Alert Service Bulletin 757-29A0066,
Revision 1, dated March 8, 2010 (for Model 757 airplanes), expanded the
airplane effectivity to include all Model 757 airplanes; no additional
work is specified in this revision of the service information. We have
not changed this AD in this regard.
Request To Revise the Costs of Compliance Paragraph
Delta Air Lines (DAL) requested that the manpower and cost for
materials specified in Hamilton Sundstrand Service Bulletin 729548-29-
18, dated February 10, 2010, be added to the ``Costs of Compliance''
paragraph in the SNPRM (79 FR 22777, April 24, 2014). DAL stated that
after reviewing the service information and comparing the costs to the
SNPRM, two discrepancies were noted. DAL stated that in Hamilton
Sundstrand Service Bulletin 729548-29-18, dated February 10, 2010, it
states, ``For a turbine assembly or RAT with a missing balance washer,
or with a balance washer screw that cannot be removed in its entirety,
a maximum of 9.0 man-hours will be required to disassemble the unit as
necessary to remove the fractured screw and balance washer, balance the
turbine assembly, assemble the unit, and test the unit.'' DAL stated
that the 9 man-hour requirement and the cost for materials are not
specified in the SNPRM's ``Costs of Compliance'' paragraph.
We agree that the labor costs specified in Hamilton Sundstrand
Service Bulletin 729548-29-18, dated February 10, 2010, were not
included in the ``Cost of Compliance'' paragraph in the SNPRM (79 FR
22777, April 24, 2014). We have revised the ``Costs of Compliance''
paragraph in this final rule to include 9 work-hours for the
replacement of balance washer screws. However, Hamilton Sundstrand
Service Bulletin 729548-29-18, dated February 10, 2010, does not
specify material costs and we have received no definitive data on
replacement costs.
In addition, UTC Aerospace Systems has stated it will continue to
cover certain costs associated with the service information free of
charge for 24 months after the effective date of this final rule,
extending the expiration dates in the service information. We have also
added a warranty statement to the ``Costs of Compliance'' paragraph of
this final rule.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM (79 FR 22777, April 24, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (79 FR 22777, April 24, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed the following service information. The service
information describes procedures for an inspection to determine the
part number and serial number of the RAT hub assembly and replacement
of the RAT or RAT hub assembly.
Boeing Alert Service Bulletin 757-29A0066, Revision 1,
dated March 8, 2010.
Boeing Alert Service Bulletin 767-29A0110, Revision 1,
dated March 8, 2010.
Boeing Special Attention Service Bulletin 757-29-0069,
dated June 24, 2010.
Boeing Special Attention Service Bulletin 767-29-0112,
dated June 24, 2010.
We have also reviewed Hamilton Sundstrand Service Bulletin 729548-
29-15, dated November 30, 2005; and Hamilton Sundstrand Service
Bulletin 730814-29-12, dated November 30, 2005. The service information
describes procedures for rework and re-identification of RAT hub
assemblies.
In addition, we have also reviewed Hamilton Sundstrand Service
Bulletin 729548-29-18, dated February 10, 2010; and Hamilton Sundstrand
Service Bulletin 730814-29-15, dated February 10, 2010. The service
information describes procedures for a general visual inspection for
missing washers and fractured screws of the rotor assembly and
replacement of balance washer screws; and inspection, rework, and re-
identification of RAT hub assemblies.
This service information is reasonably available; see ADDRESSES for
ways to access this service information.
Costs of Compliance
We estimate that this AD affects 1,132 airplanes of U.S. registry.
[[Page 13489]]
We estimate the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection.......................... 1 work-hour x $85 per $0 $85 $96,220
hour = $85.
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We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Replacement of balance washer screws... Up to 9 work-hours x $85 \1\ $0 Up to $765.
per hour = Up to $765.
Removal and installation of RAT 5 work-hours x $85 per 0 $425.
assembly. hour = $425.
Removal and installation of RAT hub 2 work-hours x $85 per 0 $170.
assembly. hour = $170.
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\1\ We have received no definitive data on replacement costs.
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all labor costs in our cost
estimate. However, we have received no definitive data that would
enable us to provide cost estimates for the on-condition parts cost
specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect 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.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2015-05-01 The Boeing Company: Amendment 39-18111; Docket No. FAA-
2008-0561; Directorate Identifier 2007-NM-223-AD.
(a) Effective Date
This AD is effective April 20, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, -200PF,
-200CB, and -300 series airplanes; and Model 767-200, -300, -300F,
and -400ER series airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 29, Hydraulic
Power.
(e) Unsafe Condition
This AD was prompted by reports indicating that the
counterweights in some hub assemblies of the ram air turbine (RAT)
could be understrength and fracture when the RAT is rotating, and
that some RAT hub assemblies were delivered with balance washer
retention screws that were incorrectly heat-treated, and therefore,
susceptible to fracture and cracking. We are issuing this AD to
prevent an inoperative RAT, which, following a dual engine shutdown
in flight, will cause loss of all hydraulic power to the primary
flight controls, resulting in subsequent loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Replacement of Parts With a Counterweight Defect
Prior to the next RAT backdrive test, or within 24 months after
the effective date of this AD, whichever occurs first: Do an
inspection to determine the part number and serial number of the RAT
hub assembly, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 757-29A0066, Revision 1, dated March
8, 2010 (for Model 757 airplanes); or Boeing Alert Service Bulletin
767-29A0110,
[[Page 13490]]
Revision 1, dated March 8, 2010 (for Model 767 airplanes). A review
of airplane maintenance records is acceptable in lieu of this
inspection if the part number and serial number of the RAT hub
assembly can be conclusively determined from that review.
(1) If the part number or serial number of the RAT hub assembly
is missing, or if the part number and serial number are specified in
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, and the hub assembly
has not been reworked and re-identified as specified in Hamilton
Sundstrand Service Bulletin 730814-29-12, dated November 30, 2005
(for Model 757 airplanes); or Hamilton Sundstrand Service Bulletin
729548-29-15, dated November 30, 2005 (for Model 767 airplanes):
Prior to the next RAT backdrive test or within 24 months after the
effective date of this AD, whichever occurs first, replace the RAT
or RAT hub assembly with a new, serviceable, or reworked and re-
identified RAT or RAT hub assembly, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
29A0066, Revision 1, dated March 8, 2010 (for Model 757 airplanes);
or Boeing Alert Service Bulletin 767-29A0110, Revision 1, dated
March 8, 2010 (for Model 767 airplanes); except as provided by
paragraphs (g)(2) and (g)(3) of this AD.
(i) Model 757-200, -200PF, -200CB, and -300 series airplanes
having part number (P/N) 733785A or 733785B, and serial number (S/N)
0410 through 0413 inclusive, 0415, 0417 through 0430 inclusive,
0432, or 0434.
(ii) Model 767-200, -300, -300F, and -400ER series airplanes
having P/N 734350A, 734350B, 734350C, or 734350D; and S/N 0666, 0673
through 0684 inclusive, 0686, 0687, or 0689.
(2) Where Boeing Alert Service Bulletin 757-29A0066, Revision 1,
dated March 8, 2010 (for Model 757 airplanes); or Boeing Alert
Service Bulletin 767-29A0110, Revision 1, dated March 8, 2010 (for
Model 767 airplanes); specifies to contact Hamilton Sundstrand for a
replacement unit, this AD does not require that action.
(3) Where Boeing Alert Service Bulletin 757-29A0066, Revision 1,
dated March 8, 2010 (for Model 757 airplanes); or Boeing Alert
Service Bulletin 767-29A0110, Revision 1, dated March 8, 2010 (for
Model 767 airplanes); specifies to return all RAT hub assemblies to
Hamilton Sundstrand for rework and test, operators may return the
RAT or RAT hub assembly to Hamilton Sundstrand or to an FAA-approved
repair facility that has the capability to disassemble, repair,
balance, and test the RAT or RAT hub assembly.
(h) Inspection and Replacement of Parts With a Balance Washer Screw
Defect
Prior to the next RAT backdrive test, or within 24 months after
the effective date of this AD, whichever occurs first: Do an
inspection to determine the part number and serial number on the RAT
hub assembly, in accordance with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 757-29-0069, dated June
24, 2010 (for Model 757 airplanes); or Boeing Special Attention
Service Bulletin 767-29-0112, dated June 24, 2010 (for Model 767
airplanes). A review of airplane maintenance records is acceptable
in lieu of this inspection if the part number and serial number of
the RAT hub assembly can be conclusively determined from that
review.
(1) If the part number or serial number of the RAT hub assembly
is missing or if the part number and serial number is listed in
paragraph 1.A., ``Effectivity,'' of Hamilton Sundstrand Service
Bulletin 730814-29-15, dated February 10, 2010 (for Model 757
airplanes); or Hamilton Sundstrand Service Bulletin 729548-29-18,
dated February 10, 2010 (for Model 767 airplanes); and the RAT hub
assembly has not been reworked and re-identified, as specified in
Hamilton Sundstrand Service Bulletin 730814-29-15, dated February
10, 2010 (for Model 757 airplanes); or Hamilton Sundstrand Service
Bulletin 729548-29-18, dated February 10, 2010 (for Model 767
airplanes): Prior to the next RAT backdrive test or within 24 months
after the effective date of this AD, whichever occurs first, do a
general visual inspection of the 12 balance washer screws installed
around the perimeter of the rotor assembly for missing washers and
fractured screws, in accordance with the Accomplishment Instructions
of Hamilton Sundstrand Service Bulletin 730814-29-15, dated February
10, 2010 (for Model 757 airplanes); or Hamilton Sundstrand Service
Bulletin 729548-29-18, dated February 10, 2010 (for Model 767
airplanes).
(2) If, during any inspection required by paragraph (h)(1) of
this AD, any balance washer is missing or any fractured screw is
found, prior to the next RAT backdrive test or within 24 months
after the effective date of this AD, whichever occurs first: Replace
the RAT or RAT hub assembly with a new, serviceable, or reworked and
re-identified RAT or RAT hub assembly, in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 757-29-0069, dated June 24, 2010 (for Model 757 airplanes);
or Boeing Special Attention Service Bulletin 767-29-0112, dated June
24, 2010 (for Model 767 airplanes); except as provided by paragraphs
(h)(2)(i), (h)(2)(ii), and (h)(2)(iii) of this AD.
(i) Where Boeing Special Attention Service Bulletin 757-29-0069,
dated June 24, 2010 (for Model 757 airplanes); and Boeing Special
Attention Service Bulletin 767-29-0112, dated June 24, 2010 (for
Model 767 airplanes); specify to contact Hamilton Sundstrand for a
replacement unit, this AD does not require that action.
(ii) Where Boeing Special Attention Service Bulletin 757-29-
0069, dated June 24, 2010 (for Model 757 airplanes); and Boeing
Special Attention Service Bulletin 767-29-0112, dated June 24, 2010
(for Model 767 airplanes); instruct operators to return all RAT or
RAT hub assemblies to Hamilton Sundstrand for rework and test,
operators may return the RAT or RAT hub assembly to Hamilton
Sundstrand or an FAA-approved repair facility that has the
capability to disassemble, repair, balance, and test the RAT or RAT
hub assembly.
(iii) Where Hamilton Sundstrand Service Bulletin 730814-29-15,
dated February 10, 2010 (for Model 757 airplanes); or Hamilton
Sundstrand Service Bulletin 729548-29-18, dated February 10, 2010
(for Model 767 airplanes); instructs operators to return all of the
removed screws (including the remnants of the fractured screws) to
Hamilton Sundstrand for further investigation, this AD does not
include that requirement.
(3) If, during any inspection required by paragraph (h)(1) of
this AD, there are no missing balance washers and no fractured
screws: Prior to the next RAT backdrive test or within 24 months
after the effective date of this AD, whichever occurs first, replace
the balance washer screws, one at a time, in accordance with
Hamilton Sundstrand Service Bulletin 730814-29-15, dated February
10, 2010 (for Model 757 airplanes); or Hamilton Sundstrand Service
Bulletin 729548-29-18, dated February 10, 2010 (for Model 767
airplanes).
(i) Parts Installation Limitations
(1) As of the effective date of this AD, no person may install a
RAT hub assembly having any part number and serial number specified
in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, on any airplane,
unless it has been reworked and re-identified in accordance with
Hamilton Sundstrand Service Bulletin 730814-29-12, dated November
30, 2005 (for Model 757 airplanes); or Hamilton Sundstrand Service
Bulletin 729548-29-15, dated November 30, 2005 (for Model 767
airplanes).
(i) Model 757-200, -200PF, -200CB, and -300 series airplanes
having P/N 733785A or 733785B; and S/N 0410 through 0413 inclusive,
0415, 0417 through 0430 inclusive, 0432, or 0434.
(ii) Model 767-200, -300, -300F, and -400ER series airplanes
having P/N 734350A, 734350B, 734350C, or 734350D, and S/N 0666, 0673
through 0684 inclusive, 0686, 0687, or 0689.
(2) As of the effective date of this AD, no person may install a
RAT hub assembly having any applicable part number and serial number
specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD, on any
airplane, unless it has been inspected, reworked, and re-identified
in accordance with Hamilton Sundstrand Service Bulletin 730814-29-
15, dated February 10, 2010 (for Model 757 airplanes); or Hamilton
Sundstrand Service Bulletin 729548-29-18, dated February 10, 2010
(for Model 767 airplanes).
(i) Model 757-200, -200PF, -200CB, and -300 series airplanes
having P/N 733785AB Series, and S/N 0107, 0105, 0121, 0151, 0179,
0204, 0282, 0289, 0296, 0315, 0319, 0337, 0390, 0403, 0412, 0421,
0424, 0426, 0429, 0430, 0439, 0445, 0450, 0477, 0503, 0510, 0512,
0584, 0585, 0591, 0599, 0609, 0617, 0624, 0656, 0673, 0685, 0789,
0822, 0841, 0854, 0911, 0912, 0936, 0957, 0961, 0971, 1061, 1064,
1096, 1101, 1102, 1105, 1113, 1117, 1170, 1172, 1173, or X2069.
(ii) Model 767-200, -300, -300F, and -400ER series airplanes
having P/N 734350 Series, and S/N 0042, 0074, 0170, 0183, 0207,
0311, 0312, 0324, 0336, 0337, 0347, 0367, 0372, 0379, 0381, 0391,
0427, 0431, 0469, 0495, 0500, 0530, 0531, 0533, 0538, 0539, 0550,
0551, 0575, 0584, 0619, 0626, 0666, 0670, 0676, 0690, 0700, 0701,
0734, 0750, 0800, 0801, 0813, 0835, 0836, 0908, 0923,
[[Page 13491]]
0958, 0968, 0980, 1009, 1012, 1019, 1046, 1052, 1054, 1102, 1127,
1167, 1264, 1285, 1300, 1317, 1322, 1362, 1372, 1394, 1398, 1436,
1594, 1633, 1634, 1635, 1636, 1637, 1638, 1639, 1640, 1641, 1642,
1643, 1644, 1645, 1646, 1647, 1648, 1649, 1650, 1651, 1652, or
X2063.
(3) As of the effective date of this AD, no person may install a
balance washer screw having P/N MS24667-14, on the RAT hub assembly
of any airplane unless it can be positively determined from a
records review that the screws did not come from Northeast
Fasteners, lots 24057 and 30533.
(j) No Information Submission
Although Boeing Alert Service Bulletin 757-29A0066, Revision 1,
dated March 8, 2010 (for Model 757 airplanes); and Boeing Alert
Service Bulletin 767-29A0110, Revision 1, dated March 8, 2010 (for
Model 767 airplanes); specify to submit information to the
manufacturer, this AD does not include that requirement.
(k) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraph (k)(1) or (k)(2) of this AD, as applicable. These
documents are not incorporated by reference in this AD.
(1) Boeing Alert Service Bulletin 757-29A0066, dated January 2,
2007 (for Model 757-200 and -200PF series airplanes).
(2) Boeing Alert Service Bulletin 767-29A0110, dated January 2,
2007 (for Model 767-200 and -300 series airplanes).
(l) Alternative Methods of Compliance (AMOCs)
(1) For Boeing Model 757-200, -200PF, -200CB, and -300 series
airplanes: The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (m)(1) of this AD.
Information may be emailed to: [email protected].
(2) For Boeing Model 767-200, -300, -300F, and -400ER series
airplanes: The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (m)(2) of this AD.
Information may be emailed to: [email protected].
(3) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(4) For Boeing Model 757-200, -200PF, -200CB, and -300 series
airplanes: An AMOC that provides an acceptable level of safety may
be used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Los Angeles ACO, to
make those findings. For a repair method to be approved, the repair
must meet the certification basis of the airplane and the approval
must specifically refer to this AD.
(5) For Boeing Model 767-200, -300, -300F, and -400ER series
airplanes: An AMOC that provides an acceptable level of safety may
be used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(m) Related Information
(1) For more information about Boeing Model 757-200, -200PF, -
200CB, and -300 series airplanes in this AD, contact: Jerry Ramos,
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5296; fax: 562-627-5210; email: [email protected].
(2) For more information about Boeing Model 767-200, -300, -
300F, and -400ER series airplanes in this AD, contact Douglas Tsuji,
Senior Aerospace Engineer, Systems and Equipment Branch, ANM-130S,
FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356;
telephone: 425-917-6546; fax: 425-917-6590; [email protected].
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (n)(3) and (n)(5) of this AD.
(n) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 757-29A0066, Revision 1, dated
March 8, 2010.
(ii) Boeing Alert Service Bulletin 767-29A0110, Revision 1,
dated March 8, 2010.
(iii) Boeing Special Attention Service Bulletin 757-29-0069,
dated June 24, 2010.
(iv) Boeing Special Attention Service Bulletin 767-29-0112,
dated June 24, 2010.
(v) Hamilton Sundstrand Service Bulletin 729548-29-15, dated
November 30, 2005.
(vi) Hamilton Sundstrand Service Bulletin 729548-29-18, dated
February 10, 2010.
(vii) Hamilton Sundstrand Service Bulletin 730814-29-12, dated
November 30, 2005.
(viii) Hamilton Sundstrand Service Bulletin 730814-29-15, dated
February 10, 2010.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; email
[email protected]; Internet https://www.myboeingfleet.com.
(4) For Hamilton Sundstrand service information identified in
this AD, contact Hamilton Sundstrand, Technical Publications, Mail
Stop 302-9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, IL 61125-
7002; phone: 860-654-3575; fax: 860-998-4564; email:
[email protected]; Internet: http://www.hamiltonsundstrand.com.
(5) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on February 23, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-05035 Filed 3-13-15; 8:45 am]
BILLING CODE 4910-13-P