Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 23893 

or policies unless they present an 

irreconcilable conflict with this rule. 

There are no administrative procedures 

which must be exhausted prior to any 

judicial challenge to the provisions of 

this direct final rule. 

Paperwork Reduction Act 

This rule does not contain new or 

amended information collection 

requirements subject to the Paperwork 

Reduction Act of 1995 (44 U.S.C. 3501 

et seq.). It does not involve collection of 

new or additional information by the 

federal government. 

E-Government Act Compliance 

GIPSA is committed to complying 

with the E-Government Act, to promote 

the use of the Internet and other 

information technologies to provide 

increased opportunities for citizen 

access to Government information and 

services, and for other purposes. 

List of Subjects in 7 CFR Part 201 

Swine, Hogs, Incorporation by 

reference, Livestock, Measurement 

standards. 

For reasons set forth in the preamble, 

9 CFR part 201 is amended as follows: 

PART 201—REGULATIONS UNDER 

THE PACKERS AND STOCKYARDS 

ACT 

■ 1. The authority citation for part 201 

continues to read as follows: 

Authority: 7 U.S.C. 181–229c. 

■ 2. In § 201.71, paragraph (a) is revised 

to read as follows: 

§ 201.71 Scales; accurate weights, repairs, 

adjustments or replacements after 

inspection. 

(a) All scales used by stockyard 

owners, swine contractors, market 

agencies, dealers, packers, and live 

poultry dealers to weigh livestock, 

livestock carcasses, live poultry, or feed 

for the purpose of purchase, sale 

acquisition, payment, or settlement 

shall be installed, maintained, and 

operated to ensure accurate weights. 

Such scales shall meet applicable 

requirements contained in section 5.59, 

Electronic Livestock, Meat, and Poultry 

Evaluation Systems and/or Devices, 

pages 5–85 and 5–86 of the ‘‘U.S. 

Department of Commerce, National 

Institute of Standards and Technology, 

Specifications, Tolerances, and other 

Technical Requirements for Weighing 

and Measuring Devices (NIST Handbook 

44), 2013 edition’’ which is hereby 

incorporated by reference. This 

incorporation by reference was 

approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. These 

materials are incorporated as they exist 

on the date of approval and a notice of 

any change in these materials will be 

published in the Federal Register. All 

approved material is available for 

inspection at USDA, GIPSA, P&SP, 1400 

Independence Ave. SW., Washington, 

DC 20250, 202–720–7363 and is for sale 

by the National Conference of Weights 

and Measures (NCWM), 1135 M Street, 

Suite 110, Lincoln, Nebraska, 68508. 

Information on this material may be 

obtained from NCWM by calling 402– 

434–4880, by emailing nfo@ncwm.net, 

or on the Internet at http://

www.nist.gov/owm. It is also available 

for inspection at the National Archives 

and Records Administration (NARA). 

For more information on the availability 

of this material at NARA, call 202–741– 

6030 or go to http://www.archives.gov/

federal_register/code_of_federal_

regulations/ibr_locations.html. 

* * * * * 

Larry Mitchell, 

Administrator, Grain Inspection, Packers and 

Stockyards Administration. 

[FR Doc. 2014–09655 Filed 4–28–14; 8:45 am] 

BILLING CODE 3410–KD–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0425; Directorate 

Identifier 2012–NM–224–AD; Amendment 

39–17815; AD 2014–07–01] 

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 certain 

The Boeing Company Model 747 

airplanes. This AD was prompted by 

reports of cracking in particular areas of 

the bulkhead structure at body station 

(BS) 2598. This AD requires repetitive 

inspections, including post-repair and 

post-modification inspections, for 

cracking in the bulkhead structure at BS 

2598; certain one-time inspections of 

certain fasteners and support frame 

modifications on certain airplanes; 

related investigative and corrective 

actions, if necessary; and an interim 

modification that would terminate 

certain repetitive inspections. We are 

issuing this AD to detect and correct 

fatigue cracking of the BS 2598 

bulkhead structure, which could 

adversely affect the structural integrity 

of the bulkhead and the horizontal 

stabilizer support structure, and result 

in loss of controllability of the airplane. 

DATES: This AD is effective June 3, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 3, 2014 

ADDRESSES: 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. 

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–2013– 

0425; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@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 certain The Boeing 

Company Model 747 airplanes. The 

SNPRM published in the Federal 

Register on January 2, 2014 (79 FR 65). 

We preceded the SNPRM with a notice 

of proposed rulemaking (NPRM) that 

published in the Federal Register on 

May 28, 2013 (78 FR 31867). 


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The NPRM proposed to require 

repetitive inspections for cracking in the 

bulkhead splice fitting, frame supports, 

forward and aft inner chords, and floor 

support; an inspection for cracking in 

the bulkhead upper web, doubler, and 

bulkhead lower web, and corrective 

actions if necessary; and repetitive postrepair inspections of the support frame, 

and corrective actions, if necessary. For 

certain airplanes, the NPRM proposed to 

require: 

• Inspections for cracking in the 

repaired area of the bulkhead, and 

corrective actions if necessary; 

• A support frame modification and 

inspections, and related investigative 

and corrective actions, if necessary; 

• Repetitive post-repair inspections of 

the support frame and inspections for 

cracking in the hinge support, and 

related investigative and corrective 

actions if necessary; 

• A one-time inspection of the frame 

web and upper shear deck (floor 

support) chord aft side for fasteners; and 

a one-time inspection of the upper 

forward inner chord, frame support 

fitting, and splice fitting for the 

installation of certain fasteners; and 

related investigative and corrective 

actions if necessary; 

• A one-time inspection of the upper 

forward inner chord, frame support 

fitting, and splice fitting for the 

installation of certain fasteners; a onetime inspection for any repair installed 

on the left and right side of the aft inner 

chord; and related investigative and 

corrective actions, if necessary; and 

• A one-time inspection of the 

support frame outer chord for cracking, 

and repair if necessary. 

The NPRM was prompted by reports 

of cracking in the forward and aft inner 

chord of the BS 2598 bulkhead near the 

upper corners of the cutout for the 

horizontal stabilizer rear spar, and 

cracking in the bulkhead upper and 

lower web panels near the inner chord 

to shear deck connection. 

The SNPRM proposed to add an 

optional terminating action for certain 

inspections and expand the inspection 

area for certain surface and open-hole 

high frequency eddy current (HFEC) 

inspections. We are issuing this AD to 

detect and correct fatigue cracking of the 

BS 2598 bulkhead structure, which 

could adversely affect the structural 

integrity of the bulkhead and the 

horizontal stabilizer support structure, 

and result in loss of controllability of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing supported the SNPRM (79 FR 65, 

January 2, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (79 FR 65, 

January 2, 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 65, 

January 2, 2014). 

Costs of Compliance 

We estimate that this AD affects 184 

airplanes of U.S. registry. 

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 

Bulkhead (support frame) inspection .......... 49 work-hours × $85 per hour = $4,165 

per inspection cycle.

$0 $4,165 per inspection cycle.$766,360 per inspection cycle. 

Support frame modification ......................... 315 work-hours × $85 per hour = $26,775 0 26,775 ...................... Up to $4,926,600. 

Support frame upper corner fastener inspection.16 work-hours × $85 per hour = $1,360 ... 0 1,360 ........................ Up to $250,240. 

Support frame post-modification/post repair 

inspection.

200 work hours × $85 per hour = $17,000 0 17,000 ...................... 3,128,000. 

We estimate the following costs to do 

any necessary interim modification that 

would be required based on the results 

of inspection of the bulkhead specified 

in paragraph (g) of this AD. We have no 

way of determining the number of 

aircraft that might need this interim 

modification: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Interim modification ...................................................... 4 work-hours × $85 per hour = $340 ........................... $0 $340 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the corrective actions 

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 


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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): 

2014–07–01 The Boeing Company: 

Amendment 39–17815; Docket No. 

FAA–2013–0425; Directorate Identifier 

2012–NM–224–AD. 

(a) Effective Date 

This AD is effective June 3, 2014. 

(b) Affected ADs 

This AD affects AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2427, Revision 7, 

dated July 19, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in particular areas of the bulkhead 

structure at body station (BS) 2598. We are 

issuing this AD to detect and correct fatigue 

cracking of the BS 2598 bulkhead structure, 

which could adversely affect the structural 

integrity of the bulkhead and the horizontal 

stabilizer support structure, and result in loss 

of controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections of the Bulkhead (Support 

Frame) 

For airplanes on which the bulkhead 

(support frame) modification specified in 

Boeing Service Bulletin 747–53A2473 or 

Boeing Alert Service Bulletin 747–53A2837 

has not been done, and on which an interim 

modification or aft inner chord repair 

specified in Boeing Alert Service Bulletin 

747–53A2427 has not been done: At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 7, dated July 

19, 2013, except as provided by paragraph 

(m)(1), (m)(2), or (m)(3) of this AD, as 

applicable, do an open-hole and surface high 

frequency eddy current (HFEC) inspection for 

cracking in the bulkhead (support frame), 

which includes the bulkhead splice fitting, 

frame supports, forward and aft inner chords, 

floor supports, and upper and lower web 

panels; do a surface HFEC inspection for 

cracking in the bulkhead upper web 

assembly; do an open-hole and surface HFEC 

inspection for cracking in the bulkhead lower 

web assembly; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2427, Revision 7, 

dated July 19, 2013, except as required by 

paragraphs (h), (m)(4), (m)(5), and (m)(6) of 

this AD. Do all applicable corrective actions 

before further flight. Repeat the applicable 

inspections, thereafter, at the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 7, dated July 

19, 2013. Doing the modification required by 

paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(h) Interim Modification 

For airplanes in Groups 1 and 2, as 

identified in Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, on which no cracking was found 

during any inspection required by paragraph 

(g) of this AD: At the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, except as 

provided by paragraph (m)(2) of this AD, do 

the interim modification, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013. Doing the 

interim modification terminates the 

repetitive inspections required by paragraph 

(g) of this AD in the area of the modification 

only. The repetitive inspections of the 

bulkhead lower web, as specified in 

paragraph (g) of this AD, must be done. If the 

aft inner chord repair or upper web repair 

specified in Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, has been accomplished, an interim 

modification on the side of the airplane that 

has the repair is not required by this 

paragraph. 

(i) Post-Repair Inspection or Post-Interim 

Modification Inspection 

For airplanes on which an interim 

modification, aft inner chord repair, or upper 

web repair has been done, as specified in 

paragraph (g) or (h) of this AD: At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 7, dated July 

19, 2013, except as specified in paragraph 

(m)(1), (m)(2), or (m)(3) of this AD, as 

applicable, do the actions specified in 

paragraphs (i)(1) and (i)(2) of this AD, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, except as 

required by paragraph (m)(4) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013. Doing the 

modification required by paragraph (j) of this 

AD terminates the repetitive inspections 

required by this paragraph. 

(1) Do forward side surface HFEC 

inspections for cracking of the bulkhead 

forward inner chord, splice fitting, and frame 

support. 

(2) Do surface and open-hole HFEC 

inspections for cracking in the repaired and 

modified areas of the bulkhead, as 

applicable. 

(j) Bulkhead (Support Frame) Modification 

and Inspections 

For airplanes on which the bulkhead 

(support frame) modification, as specified in 

Boeing Service Bulletin 747–53A2473 has 

not been done as of the effective date of this 

AD: At the applicable time specified in tables 

2 and 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011, do the 

bulkhead (support frame) modification and 

inspections and all applicable related 

investigative and corrective actions; in 

accordance with steps 3.B.3., 3.B.4., and 

3.B.5. of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011, except 

as required by paragraph (m)(4) of this AD. 

Do all applicable related investigative and 

corrective actions before further flight. Doing 

the modification in this paragraph terminates 

the inspections required by paragraphs (g) 

and (i) of this AD. 

(k) Post-Modification Inspections 

(1) For airplanes on which the bulkhead 

(support frame) modification, as specified in 

Boeing Service Bulletin 747–53A2473 has 

been done: Except as provided by paragraphs 

(m)(7) and (m)(8) of this AD, at the applicable 


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time specified in tables 6, 7, 8, and 9 of 

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

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, do support frame 

post-modification inspections, and open-hole 

HFEC inspections for cracking in the hinge 

support, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, except as required by paragraph (m)(4) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable times specified in 

tables 6, 7, 8, and 9 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(2) For airplanes on which the support 

frame modification, as specified in Boeing 

Service Bulletin 747–53A2473, Revision 1, 

dated February 20, 2007 (which is not 

incorporated by reference in this AD), has 

been done: Except as specified in paragraphs 

(m)(7) and (m)(8) of this AD, at the applicable 

time specified in tables 4 and 5 of paragraph 

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

Bulletin 747–53A2473, Revision 4, dated 

December 1, 2011, do a one-time general 

visual inspection of the frame web and upper 

shear deck (floor support) chord aft side for 

fasteners that were installed as part of an 

inner chord repair removal; and a one-time 

general visual inspection of the upper 

forward inner chord, frame support fitting, 

and splice fitting for the installation of 

certain fasteners; and do all applicable 

related investigative and corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, except as required by paragraph (m)(4) 

of this AD. Do all applicable related 

investigative and corrective actions at the 

applicable times specified in tables 4 and 5 

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

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011. 

(3) For airplanes on which the support 

frame modification, as specified in Boeing 

Service Bulletin 747–53A2473, dated March 

24, 2005 (which was incorporated by 

reference in AD 2006–05–06, Amendment 

39–14503 (71 FR 12125, March 9, 2006)), has 

been done: Except as specified in paragraphs 

(m)(7) and (m)(8) of this AD, at the applicable 

time specified in tables 5 and 10 of paragraph 

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

Bulletin 747–53A2473, Revision 4, dated 

December 1, 2011, do a one-time general 

visual inspection of the upper forward inner 

chord, frame support fitting, and splice 

fitting for the installation of certain fasteners; 

a one-time general visual inspection for any 

repair installed on the left and right side of 

the aft inner chord; and do all applicable 

related investigative and corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, except as required by paragraph (m)(4) 

of this AD. Do all applicable related 

investigative and corrective actions at the 

applicable times specified in tables 5 and 10 

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

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011. 

(4) For airplanes on which a postmodification inspection was done using 

paragraph 3.B.8. of Part 1 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 3, 

dated July 14, 2011 (which is not 

incorporated by reference in this AD): Except 

as required by paragraphs (m)(7) and (m)(8) 

of this AD, at the applicable time in table 11 

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

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, do a one-time 

surface HFEC inspection of the support frame 

outer chord for cracking, in accordance with 

Part 1 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011. If any 

cracking is found, repair before further flight, 

using a method approved in accordance with 

the procedures specified in paragraph (q) of 

this AD. 

(l) Post-Modification and Post-Repair 

Inspections 

For airplanes on which cracking was found 

during a post-modification inspection and 

was repaired by doing the installation of an 

upper or lower corner post-modification web 

crack repair, as specified in Boeing Service 

Bulletin 747–53A2473, Revision 4, dated 

December 1, 2011: At the applicable times 

specified in tables 6 and 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011, do a bulkhead (support frame) postrepair inspection, and do all applicable 

corrective actions, in accordance with 

paragraph a., b., or c. of Part 4 of paragraph 

3.B.8 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011, as 

applicable, except as required by paragraph 

(m)(4) of this AD. Repeat the inspection, 

thereafter, at the applicable times specified in 

tables 6 and 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(m) Exceptions to Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies a compliance time after ‘‘the 

date on Revision 2 of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after August 28, 

2001 (the effective date of AD 2001–15–03, 

Amendment 39–12337 (66 FR 38365, July 24, 

2001)). 

(2) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies a compliance time after ‘‘the 

date on Revision 4 of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after August 5, 

2010 (the effective date of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010)). 

(3) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies a compliance time ‘‘after the 

date on the respective service bulletin 

revision’’ this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

(4) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013; or Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011; specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

(5) If, during any inspection required by 

paragraph (g) of this AD, any cracking is 

found in the bonded web doubler, before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

(6) Where Part 1 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies accomplishing inspections for 

cracking in the forward and aft inner chords, 

splice fittings, floor supports, and upper and 

lower web panels, this AD also requires 

doing an open-hole HFEC inspection of the 

bonded web doubler if present. 

(7) Where Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, specifies a compliance time ‘‘after the 

date on Revision 2 of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time as of August 5, 

2010 (the effective date of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010)). 

(8) Where Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, specifies a compliance time ‘‘after the 

date on Revision 3 of this service bulletin,’’ 

or ‘‘after the date on Revision 4 of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time ‘‘after 

the effective date of this AD.’’ 

(n) Optional Terminating Modification 

Accomplishing the modification of the 

bulkhead at BS 2598 in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2837, dated July 13, 

2012, terminates the requirements of 

paragraphs (g), (h), (i), (j), (k), and (l) of this 

AD, except where Boeing Alert Service 

Bulletin 747–53A2837, dated July 13, 2012, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair the crack 

using a method approved in accordance with 

the procedures specified in paragraph (q) of 

this AD. 

(o) Terminating Action for Certain 

Requirements of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010) 

(1) Accomplishing the inspections, repairs, 

and modification in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, is an acceptable 

terminating action for the corresponding 

inspections, repairs, and modification at the 

BS 2598 support frame required by 

paragraphs (i), (j), (k), (1), (m), (n), (o), (p), (q), 

(r), (s), (t), (u), and (v) of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010). Where Boeing Service Bulletin 747– 


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53A2473, Revision 4, dated December 1, 

2011, specifies to contact Boeing for repair 

instructions, the repair instructions must be 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. All 

provisions of AD 2010–14–07 that are not 

specifically referenced in this paragraph 

remain fully applicable and must be 

complied with. 

(2) Accomplishing the inspections, repairs, 

and interim modification in accordance with 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, is an 

acceptable terminating action for the 

corresponding inspections, repairs and 

interim modification at the BS 2598 bulkhead 

required by paragraphs (i), (j), (o), (s), (t), (u), 

and (v) of AD 2010–14–07, Amendment 39– 

16352 (75 FR 38001, July 1, 2010). Where 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, specifies to 

contact Boeing for repair data, the repair data 

must be approved in accordance with the 

procedures specified in paragraph (q) of this 

AD. All provisions of AD 2010–14–07 that 

are not specifically referenced in this 

paragraph remain fully applicable and must 

be complied with. 

(p) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), 

and (n)(2) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2427, Revision 6, dated July 14, 2011, 

provided that the additional actions added in 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, are done 

within the applicable compliance times 

specified in paragraphs (g), (h), and (i) of this 

AD. Boeing Alert Service Bulletin 747– 

53A2427, Revision 6, dated July 14, 2011, is 

not incorporated by reference in this AD. 

(q) 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 (r)(1) 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) Related portions or applicable 

paragraphs of AMOCs approved previously 

in accordance with AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010), are approved as AMOCs for the 

corresponding provisions of paragraphs (g), 

(h), (i), (j), (k), and (l) of this AD. All new 

actions specified in paragraphs (g), (h), (i), (j), 

(k), and (l) of this AD that are not identified 

in a previously approved AMOC must still be 

done. 

(r) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6428; fax: 425–917–6590; email: 

nathan.p.weigand@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be viewed at the addresses 

specified in paragraphs (s)(3) and (s)(4) of 

this AD. 

(s) 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 747– 

53A2427, Revision 7, dated July 19, 2013. 

(ii) Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011. 

(iii) Boeing Alert Service Bulletin 747– 

53A2837, dated July 13, 2012. 

(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. 

(4) 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. 

(5) 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 

17, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–07339 Filed 4–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0020; Directorate 

Identifier 2013–CE–039–AD; Amendment 

39–17821; AD 2014–07–07] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

airworthiness directive (AD) 87–02–04 

for British Aerospace (Operations) 

Limited Model HP.137 Jetstream MK.1, 

Jetstream Series 200, and Jetstream 

Series 3101 airplanes. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as cracking of the forward 

main landing gear yoke pintle resulting 

from corrosion pits leading to stress 

corrosion. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective June 3, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 3, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0020; or in person at the 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 service information identified in 

this AD, contact BAE Systems 

(Operations) Ltd, Customer Information 

Department, Prestwick International 

Airport, Ayrshire, KA9 2RW, Scotland, 

United Kingdom; phone: +44 1292 

675207, fax: +44 1292 675704; email: 

RApublications@baesystems.com; 

Internet: http://

www.jetstreamcentral.com. You may 

view this referenced service information 

at the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 


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