Document ID: FAA-2008-0561-0015
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2015-03-16T04:00Z

[Federal Register Volume 80, Number 50 (Monday, March 16, 2015)]
[Rules and Regulations]
[Pages 13486-13491]
From the Federal Register Online via the Government Printing 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 
me.boecom@boeing.com; 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: tech.solutions@hs.utc.com; 
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; Douglas.Tsuji@faa.gov.

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
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection..........................  1 work-hour x $85 per                $0              $85          $96,220
                                       hour = $85.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                 Action                          Labor cost            Parts cost          Cost per product
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
\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: 9-ANM-LAACO-AMOC-REQUESTS@faa.gov.
    (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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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: Jerry.Ramos@faa.gov.
    (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; Douglas.Tsuji@faa.gov.
    (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 
me.boecom@boeing.com; 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: 
tech.solutions@hs.utc.com; 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