73460 Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules 

Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, until 

accomplishment of the requirements of 

paragraph (h) of this AD. 

(h) Modification 

For airplanes that have not been modified 

as specified in Boeing Service Bulletin 747– 

53–2088: At the applicable time specified in 

Table 1 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, except as 

required by paragraph (j)(1) of this AD, 

modify the tension ties, including doing an 

open-hole high frequency eddy current 

inspection for cracks, as applicable, and all 

applicable corrective actions, in accordance 

with Part III of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, except as required by paragraph (j)(2) 

of this AD. All applicable corrective actions 

must be done before further flight. This 

modification terminates the repetitive 

inspection requirements of paragraph (g) of 

this AD. 

(i) Post-Modification Repetitive Inspections 

For airplanes that have been modified as 

specified in Boeing Service Bulletin 747–53– 

2088: At the applicable time in Table 2 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2088, 

Revision 4, dated January 11, 2013, do a 

detailed inspection for cracking of the 

tension tie at BS 760 or 780, and do all 

applicable corrective actions, in accordance 

with Part I of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, except as required by paragraph (j)(2) 

of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

inspection thereafter at the applicable time in 

Table 2 specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2088, Revision 4, dated 

January 11, 2013. Boeing Alert Service 

Bulletin 747–53A2088, Revision 4, dated 

January 11, 2013, notes that additional postmodification inspections are specified in 

Boeing Service Bulletin 747–53A2502; those 

post-modification inspections are required by 

AD 2006–01–07, Amendment 39–14446 (71 

FR 1947, January 12, 2006). 

(j) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, specifies a compliance time ‘‘after the 

Revision 4 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2088, Revision 4, dated January 11, 

2013, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in this AD, if those actions 

were performed before the effective date of 

this AD using Boeing Alert Service Bulletin 

747–53A2088, Revision 3, dated September 

8, 1994. 

(l) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) 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 (n)(2) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) 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. 

(4) AMOCs approved for AD 84–19–01, 

Amendment 39–4913 (49 FR 35365, 

September 17, 1984), are approved as 

AMOCs for the corresponding requirements 

of paragraph (g) (the retained detailed 

inspections) and paragraph (i) of this AD, but 

not as AMOCs for the high frequency eddy 

current inspections required by paragraph (g) 

of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Roger Caldwell, Aerospace Engineer, 

Denver Aircraft Certification Office, FAA, 

26805 East 68th Avenue, Denver, CO 80249; 

phone: 303–342–1086; fax: 303–342–1088; 

email: Roger.Caldwell@faa.gov. 

(2) For information about AMOCs, contact 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6428; fax: 425–917–6590; 

email: Nathan.P.Weigand@faa.gov. 

(3) For 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; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on 

November 29, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–29128 Filed 12–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0978; Directorate 

Identifier 2013–NM–120–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–400ER 

series airplanes. This proposed AD was 

prompted by reports of turbine wheel 

bursts in the air driven pump (ADP) 

turbine gearbox assembly (TGA), which 

resulted in the release of high energy 

fragments. This proposed AD would 

require replacing the existing ADP TGA 

with an improved ADP TGA. We are 

proposing this AD to prevent fragments 

from an uncontained turbine wheel 

burst penetrating the fuselage and 

striking passengers, or penetrating the 

wing-to-body fairing and striking 

ground handling or maintenance 

personnel, causing serious injury. 

DATES: We must receive comments on 

this proposed AD by January 21, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules 73461 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6468; 

fax: 425–917–6190; email: 

kenneth.frey@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0978; Directorate Identifier 2013– 

NM–120–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received reports of uncontained 

failures of the turbine wheel in the ADP 

TGA assembly. Flightcrews noticed a 

reduction in center hydraulic system 

pressure and upon landing, found 

damage to the ADP TGA assembly, the 

left, aft, wing-to-body fairing, and to the 

airplane skin. Boeing’s analysis 

determined that the existing ADP TGA 

assembly design cannot adequately 

contain fragments caused by a turbine 

wheel burst. Fragments from an 

uncontained turbine wheel burst could 

penetrate the fuselage and strike 

passengers, or penetrate the wing-tobody fairing and strike ground handling 

or maintenance personnel, causing 

serious injury. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 767–29– 

0113, dated May 29, 2013. For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2013–0978. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information identified 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 37 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement ........................... 7 work-hours × $85 per hour = $595 ..................................... $114,705 $115,300 $4,266,100 

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 proposed 

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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
73462 Federal Register / Vol. 78, No. 235 / Friday, December 6, 2013 / Proposed Rules 

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): 

The Boeing Company: Docket No. FAA– 

2013–0978; Directorate Identifier 2013– 

NM–120–AD. 

(a) Comments Due Date 

We must receive comments by January 21, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–400ER series airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

767–29–0113, dated May 29, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 29, Hydraulic Power. 

(e) Unsafe Condition 

This AD was prompted by reports of 

turbine wheel bursts in the air driven pump 

(ADP) turbine gearbox assembly (TGA), 

which resulted in the release of high energy 

fragments. We are issuing this AD to prevent 

fragments from an uncontained turbine 

wheel burst penetrating the fuselage and 

striking passengers, or penetrating the wingto-body fairing and striking ground handling 

or maintenance personnel, causing serious 

injury. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement of Turbine Gearbox 

Assembly 

Except as required by paragraph (i) of this 

AD: At the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 767–29–0113, dated May 29, 

2013, replace the existing ADP TGA having 

part number N012000000 or N012000000–1 

with an improved ADP TGA having part 

number N012000000–2 or N012000000–3, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 767–29–0113, dated May 29, 

2013. 

Note 1 to paragraph (g) of this AD: 

Guidance on modifying an existing ADP TGA 

so it can be re-identified as part number 

N012000000–2 or N012000000–3 can be 

found in Fairchild Controls Service Bulletin 

N012000000–29–03, Revision 2, dated 

January 29, 2013. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an ADP TGA having part 

number N012000000 or N012000000–1 on 

any airplane. 

(i) Exception to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 767–29–0113, dated May 29, 2013, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) 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 (k) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6468; fax: 425–917– 

6190; email: kenneth.frey@faa.gov. 

(2) For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P. O. Box 3707, 

MC2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; Internet https://

www.myboeingfleet.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

November 26, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–29136 Filed 12–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1024; Directorate 

Identifier 2013–NM–140–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This proposed AD was 

prompted by reports of a fractured wingto-fuselage strut attachment joint bolt. 

This proposed AD would require doing 

a torque check of all wing-to-fuselage 

strut attachment joint bolts, and 

repairing or replacing if necessary. For 

certain airplanes this proposed AD 

would require a detailed inspection for 

corrosion, damage, and wear of each 

wing-to-fuselage strut attachment joint 

bolt and associated hardware, and 

replacing if necessary; and a borescope 

inspection for corrosion and damage of 

the bore hole and barrel nut threads, 

and repairing or replacing if necessary. 

We are proposing this AD to detect and 

correct fractured bolts, which could 

result in reduced structural integrity of 

the wing-to-fuselage strut attachment 

joint and subsequent loss of the wing. 

DATES: We must receive comments on 

this proposed AD by January 21, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 


emcdonald on DSK67QTVN1PROD with PROPOSALS