13486 Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–18 dated 

July 16, 2013, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–0491. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(4) and (o)(5) of this AD. 

(o) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 6, 2015 (80 FR 

5017, January 30, 2015). 

(i) Bombardier Service Bulletin 604–27– 

032, Revision 02, dated April 22, 2014. 

(ii) Bombardier Service Bulletin 605–27– 

002, Revision 02, dated April 22, 2014. 

(iii) Bombardier Temporary Revision 604/ 

37, dated May 21, 2013, to the Bombardier 

Challenger CL–604 Airplane Flight Manual, 

PSP 604–1. 

(iv) Bombardier Temporary Revision 605/ 

18, dated May 21, 2013, to the Bombardier 

Challenger CL–605 Airplane Flight Manual, 

PSP 605–1. 

(4) For service information identified in 

this AD, contact Bombardier, Inc., 400 Coˆte 

Vertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(5) You may view this 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. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on March 5, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–05735 Filed 3–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

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. 

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 heattreated, 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 reidentified 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 


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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. 


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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 reidentification 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 reidentification 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. 


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We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ............................... 1 work-hour × $85 per hour = $85 ......................................... $0 $85 $96,220 

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 × $85 per hour = Up to $765 ........ 1 $0 Up to $765. 

Removal and installation of RAT assembly .................. 5 work-hours × $85 per hour = $425 ............................ 0 $425. 

Removal and installation of RAT hub assembly ........... 2 work-hours × $85 per hour = $170 ............................ 0 $170. 

1We 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 oncondition 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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, 


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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 reidentified 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 reidentified, 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 reidentified 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, 


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Federal Register / Vol. 80, No. 50 / Monday, March 16, 2015 / Rules and Regulations 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-AMOCREQUESTS@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-AMOCRequests@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.hamiltons

undstrand.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 

DEPARTMENT OF DEFENSE 

32 CFR Part 266 

RIN 0790–AJ30 

Audits of State and Local 

Governments, Institutions of Higher 

Education, and Other Nonprofit 

Institutions 

AGENCY: Department of Defense. 

ACTION: Final rule. 

SUMMARY: This final rule removes 

regulations concerning the audits of 

state and local governments, institutions 

of higher education, and other nonprofit 

institutions. The Code of Federal 

Regulations (CFR) provisions being 

removed contain policies and 

procedures directed at DoD component 

personnel and not the public. 

Additionally, other DoD guidance on 

this subject has been published in the 

Defense Grant and Agreement 

Regulations, to provide appropriate 

notice to outside entities. 

DATES: This rule is effective on March 

16, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Patricia Toppings at 571–372–0485. 


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