Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 39185 

The Privacy Act allows Government 

agencies to exempt certain records from 

the access and amendment provisions. If 

an agency claims an exemption, 

however, it must issue a Notice of 

Proposed Rulemaking to make clear to 

the public the reasons why a particular 

exemption is claimed. 

DHS is claiming exemptions from 

certain requirements of the Privacy Act 

for DHS/ALL—029 Civil Rights and 

Civil Liberties Records System of 

Records. Some information in DHS/ 

ALL—029 Civil Rights and Civil 

Liberties Records System of Records 

relates to official DHS national security, 

law enforcement, immigration, 

intelligence activities, and protective 

services to the President of the United 

States or other individuals pursuant to 

Section 3056 and 3056A of Title 18. 

These exemptions are needed to protect 

information relating to DHS activities 

from disclosure to subjects or others 

related to these activities. Specifically, 

the exemptions are required to preclude 

subjects of these activities from 

frustrating these processes; to avoid 

disclosure of activity techniques; to 

protect the identities and physical safety 

of confidential informants and law 

enforcement personnel; to ensure DHS’ 

ability to obtain information from third 

parties and other sources; to protect the 

privacy of third parties; to safeguard 

classified information; and to safeguard 

records in connection with providing 

protective services to the President of 

the United States or other individuals 

pursuant to Section 3056 and 3056A of 

Title 18. Disclosure of information to 

the subject of the inquiry could also 

permit the subject to avoid detection or 

apprehension. 

The exemptions proposed here are 

standard law enforcement and national 

security exemptions exercised by a large 

number of federal law enforcement and 

intelligence agencies. In appropriate 

circumstances, where compliance 

would not appear to interfere with or 

adversely affect the law enforcement 

purposes of this system and the overall 

law enforcement process, the applicable 

exemptions may be waived on a case by 

case basis. 

A notice of system of records for DHS/ 

ALL—029 Civil Rights and Civil 

Liberties Records System of Records is 

also published in this issue of the 

Federal Register. 

List of Subjects in 6 CFR Part 5 

Freedom of information; Privacy. 

For the reasons stated in the 

preamble, DHS proposes to amend 

Chapter I of Title 6, Code of Federal 

Regulations, as follows: 

PART 5—DISCLOSURE OF RECORDS 

AND INFORMATION 

1. The authority citation for Part 5 

continues to read as follows: 

Authority: 6 U.S.C. 101 et seq.; Pub. L. 

107–296, 116 Stat. 2135; 5 U.S.C. 301. 

Subpart A also issued under 5 U.S.C. 552. 

Subpart B also issued under 5 U.S.C. 552a. 

2. Add to Appendix C to Part 5 the 

following new paragraph ‘‘49’’: 

Appendix C to Part 5—DHS Systems of 

Records Exempt From the Privacy Act 

* * * * * 

49. The DHS/ALL—029 Civil Rights and 

Civil Liberties Records System of Records 

consists of electronic and paper records and 

will be used by DHS and its components. The 

DHS/ALL—029 Civil Rights and Civil 

Liberties Records System of Records is a 

repository of information held by DHS in 

connection with its several and varied 

missions and functions, including, but not 

limited to the enforcement of civil and 

criminal laws; investigations, inquiries, and 

proceedings thereunder; national security 

and intelligence activities; and protection of 

the President of the United States or other 

individuals pursuant to Section 3056 and 

3056A of Title 18. The DHS/ALL—029 Civil 

Rights and Civil Liberties Records System of 

Records contains information that is 

collected by, on behalf of, in support of, or 

in cooperation with DHS and its components 

and may contain personally identifiable 

information collected by other federal, state, 

local, tribal, foreign, or international 

government agencies. The Secretary of 

Homeland Security has exempted this system 

from the following provisions of the Privacy 

Act, subject to limitations set forth in 5 

U.S.C. 552a(c)(3); (d); (e)(1), (e)(4)(G), 

(e)(4)(H), (e)(4)(I); and (f) pursuant to 5 U.S.C. 

552a(k)(1), (k)(2), (k)(3), and (k)(5). 

Exemptions from these particular subsections 

are justified, on a case-by-case basis to be 

determined at the time a request is made, for 

the following reasons: 

(a) From subsection (c)(3) (Accounting for 

Disclosures) because release of the 

accounting of disclosures could alert the 

individual who is the subject of an 

investigation of an actual or potential 

criminal, civil, or regulatory violation to the 

existence of that investigation and reveal 

investigative interest on the part of DHS as 

well as the recipient agency. Disclosure of 

the accounting would, therefore, present a 

serious impediment to law enforcement 

efforts and/or efforts to preserve national 

security. Disclosure of the accounting would 

also permit the individual who is the subject 

of a record to impede the investigation, to 

tamper with witnesses or evidence, and to 

avoid detection or apprehension, which 

would undermine the entire investigative 

process. 

(b) From subsection (d) (Access to Records) 

because access to the records contained in 

this system of records could inform the 

individual who is the subject of an 

investigation of an actual or potential 

criminal, civil, or regulatory violation to the 

existence of that investigation and reveal 

investigative interest on the part of DHS or 

another agency. Access to the records could 

permit the individual who is the subject of 

a record to impede the investigation, to 

tamper with witnesses or evidence, and to 

avoid detection or apprehension. 

Amendment of the records could interfere 

with ongoing investigations and law 

enforcement activities and would impose an 

unreasonable administrative burden by 

requiring investigations to be continually 

reinvestigated. In addition, permitting access 

and amendment to such information could 

disclose security-sensitive information that 

could be detrimental to homeland security. 

(c) From subsection (e)(1) (Relevancy and 

Necessity of Information) because in the 

course of investigations into potential 

violations of federal law, the accuracy of 

information obtained or introduced 

occasionally may be unclear, or the 

information may not be strictly relevant or 

necessary to a specific investigation. In the 

interests of effective law enforcement, it is 

appropriate to retain all information that may 

aid in establishing patterns of unlawful 

activity. 

(d) From subsections (e)(4)(G), (e)(4)(H), 

and (e)(4)(I) (Agency Requirements) and (f) 

(Agency Rules), because portions of this 

system are exempt from the individual access 

provisions of subsection (d) for the reasons 

noted above, and therefore DHS is not 

required to establish requirements, rules, or 

procedures with respect to such access. 

Providing notice to individuals with respect 

to existence of records pertaining to them in 

the system of records or otherwise setting up 

procedures pursuant to which individuals 

may access and view records pertaining to 

themselves in the system would undermine 

investigative efforts and reveal the identities 

of witnesses, and potential witnesses, and 

confidential informants. 

* * * * * 

Dated: June 30, 2010. 

Mary Ellen Callahan, 

Chief Privacy Officer, Department of 

Homeland Security. 

[FR Doc. 2010–16580 Filed 7–7–10; 8:45 am] 

BILLING CODE 9110–9B–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0679; Directorate 

Identifier 2009–NM–179–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747SR, and 747SP 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


srobinson on DSKHWCL6B1PROD with PROPOSALS
39186 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP series 

airplanes. The existing AD requires 

repetitive inspections and torque checks 

of the hanger fittings and strut forward 

bulkhead of the forward engine mount 

and adjacent support structure, and 

visual inspections of the internal angle 

and external bulkhead chord and 

detailed inspection of internal angles, 

and corrective actions if necessary. The 

existing AD also provides for an 

optional inspection. This proposed AD 

would also require additional 

inspections of airplanes that have hi-lok 

bolts and collars at all of the Group B 

fastener locations, except fastener 13, 

and related investigative and corrective 

actions. This proposed AD would 

require repetitive inspections of the 

internal angle and corrective actions, if 

necessary. This proposed AD also 

would require, for certain airplanes, 

replacing the fasteners, which 

terminates certain repetitive 

inspections. This proposed AD results 

from the reports of undertorqued or 

loose fasteners, a cracked bulkhead 

chord, and a fractured back-up angle. 

We are proposing this AD to prevent 

loose fasteners and/or damaged or 

cracked hanger fittings, back-up angles, 

and bulkhead of the forward engine 

mount, which could lead to failure of 

the hanger fitting and bulkhead and 

consequent separation of the engine 

from the airplane. 

DATES: We must receive comments on 

this proposed AD by August 23, 2010. 

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 20590, 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, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; 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 or 425–227–1152. 

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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Ken 

Paoletti, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6434; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0679; Directorate Identifier 

2009–NM–179–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 

On September 14, 2007, we issued AD 

2007–19–19, Amendment 39–15210 (72 

FR 53939, September 21, 2007), for 

certain Boeing Model 747–100, 747– 

100B, 747–100B SUD, 747–200B, 747– 

200C, 747–200F, 747–300, 747SR, and 

747SP series airplanes. That AD 

requires repetitive inspections and 

torque checks of the hanger fittings and 

strut forward bulkhead of the forward 

engine mount and adjacent support 

structure, and visual inspections of the 

internal angle and external bulkhead 

chord and detailed inspection of 

internal angles, and corrective actions if 

necessary. The existing AD also 

provides for an optional inspection. 

That AD resulted from reports of 

undertorqued or loose fasteners, a 

cracked bulkhead chord, and a fractured 

back-up angle after operators 

accomplished the terminating action 

required by AD 2001–15–02, 

Amendment 39–12336 (66 FR 37884, 

July 20, 2001), which was superseded 

by AD 2007–19–19. We issued that AD 

to detect and correct loose fasteners 

and/or damaged or cracked hanger 

fittings, back-up angles, and bulkhead of 

the forward engine mount, which could 

lead to failure of the hanger fitting and 

bulkhead and consequent separation of 

the engine from the airplane. 

Actions Since Existing AD Was Issued 

The preamble to AD 2007–19–19 

specifies that we consider the 

requirements ‘‘interim action’’ and that 

we were considering requiring the 

inspections and applicable related 

investigative and corrective actions 

specified in Part 7 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–54A2203, 

Revision 1, dated August 9, 2007, and 

we have determined that further 

rulemaking is indeed necessary; this 

proposed AD follows from that 

determination. 

Relevant Service Information 

AD 2007–19–19 cited Boeing Alert 

Service Bulletin 747–54A2203, Revision 

1, dated August 9, 2007, as the relevant 

source of information. Since we issued 

AD 2007–19–19, the manufacturer has 

revised the service information. Boeing 

has released Alert Service Bulletin 747– 

54A2203, Revision 2, dated July 9, 2009. 

Boeing Alert Service Bulletin 747– 

54A2203, Revision 2, dated July 9, 2009, 

specifies that hi-lok bolts and collars at 

all of the Group B fastener locations, 

except fastener 13, need to be replaced 

with bolts specified in the service 

bulletin within 18 months after the 

service bulletin is released. (Boeing 

Alert Service Bulletin 747–54A2203, 

dated August 31, 2000; and Revision 1, 

dated August 9, 2007; specified that the 

hi-lok bolts on these airplanes did not 

have to be replaced according to Part 6 

of the Accomplishment Instructions if 

they met the inspection requirements of 

Part 2.) The related corrective actions 

are replacing the fasteners; removing 

loose fasteners; tightening all Group A 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 39187 

and Group B fasteners; tightening all 

under-torqued or loose Group A and 

Group B fasteners; and removing loose 

fasteners, inspecting the hole, installing 

fasteners, and applying optional torque 

stripes. In addition, that service bulletin 

specifies that the fasteners on these 

airplanes need to be replaced in 

accordance with Part 6—Fastener 

Replacement. The related investigative 

actions are doing repetitive detailed 

inspections, a torque stripe inspection, 

and torque checks. 

Boeing Alert Service Bulletin 747– 

54A2203, Revision 2, dated July 9, 2009, 

specifies a compliance time of within 90 

days after the date of Revision 2 of that 

service bulletin for the Part 2 

inspection, and within 18 months after 

the date of Revision 2 of that service 

bulletin for the Part 6 replacement. For 

the related investigative actions, that 

service bulletin specifies a compliance 

time ranging from before further flight to 

within 18 months after the fasteners are 

replaced. For the related corrective 

actions, that service bulletin specifies a 

compliance time ranging from before 

further flight to within 18 months after 

under-torqued or loose fasteners were 

found. 

For all airplanes, Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009, clarifies the 

requirements for conditions in which 

the torque stripe is not applied and for 

which no under-torqued or loose 

fastener was found by reordering the 

steps. In addition, Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009, adds an option for 

supporting the engine weight, instead of 

removing the engine, in Part 7—HFEC 

Internal Angle Inspection of the 

Accomplishment Instructions of that 

service bulletin. Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009, also no longer 

includes the 60-month compliance time 

for doing Part 6 of the Accomplishment 

Instructions of that service bulletin. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2007– 

19–19 and would retain certain 

requirements of the existing AD. This 

proposed AD would also require 

repetitive inspections of the internal 

angle, and corrective actions if 

necessary, and this proposed AD would 

also require, for certain airplanes, 

replacing the fasteners. 

Differences Between the Proposed AD 

and Service Information 

The service information specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD requires 

repairing those conditions in one of the 

following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization whom we 

have authorized to make those findings. 

Part 7—HFEC Internal Angle 

Inspection of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009, also provides an 

option to support the engine weight 

rather than removing the engine. This 

AD requires the removal of the engine 

to perform the inspection. 

Costs of Compliance 

There are about 266 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Actions (required by AD 2007–19–19) ............................ 40 $85 $0 $3,400 121 $411,400 

Internal Angle Inspection (new proposed action) ............ 16 85 0 1,360 121 164,560 

Replacement of fasteners (new proposed action) ........... 24 85 0 2,040 121 246,840 

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 

We have 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 that the 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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 

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: 


srobinson on DSKHWCL6B1PROD with PROPOSALS
39188 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 

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 

removing Amendment 39–15210 (72 FR 

53939, September 21, 2007) and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0679; Directorate Identifier 2009– 

NM–179–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by August 23, 2010. 

Affected ADs 

(b) This AD supersedes AD 2007–19–19, 

Amendment 39–15210. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 747–54A2203, 

Revision 2, dated July 9, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Unsafe Condition 

(e) This AD results from the development 

of a mandating action. The Federal Aviation 

Administration is issuing this AD to detect 

and correct loose fasteners and/or damaged 

or cracked hanger fittings, back-up angles, 

and bulkhead of the forward engine mount, 

which could lead to failure of the hanger 

fitting and bulkhead and consequent 

separation of the engine from the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of a Requirement of AD 2007– 

19–19, With Updated Service Information 

Inspections and Related Investigative and 

Corrective Actions 

(g) Except as provided by paragraphs (i), 

(l), and (n) of this AD: At the applicable 

compliance times and repeat intervals listed 

in Tables 1 and 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–54A2203, Revision 1, dated 

August 9, 2007, do the inspections and 

applicable related investigative and 

corrective actions in accordance with Parts 2 

and 8 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–54A2203, 

Revision 1, dated August 9, 2007; or Revision 

2, dated July 9, 2009. After the effective date 

of this AD, use only Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, dated July 

9, 2009. 

New Requirements of This AD 

Mandatory Initial and Repetitive Inspections 

and Related Investigative and Corrective 

Actions 

(h) For all airplanes: Except as provided by 

paragraph (m) of this AD, at the applicable 

time in Table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, dated July 

9, 2009, do the initial inspection and related 

investigative and corrective actions in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009, except as required by 

paragraphs (k) and (n) of this AD. Repeat the 

inspection thereafter at the applicable time in 

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

Service Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009. 

(i) For airplanes that were inspected in 

accordance with Boeing Alert Service 

Bulletin 747–54A2203, dated August 31, 

2000; or Revision 1, dated August 9, 2007; 

and that have hi-lock bolts and collars at all 

of the Group B fastener locations: Except as 

provided by paragraph (m) of this AD, at the 

applicable time in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, dated July 

9, 2009, do the initial inspection and related 

investigative and corrective actions in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009, except as required by 

paragraph (n) of this AD. Repeat the 

inspection at the applicable interval in 

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

Service Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009. 

Replacement of Hi-Lok Group B Fasteners 

(j) For airplanes that were inspected in 

accordance with Boeing Alert Service 

Bulletin 747–54A2203, dated August 31, 

2000, and that have hi-lock bolts and collars 

at all of the Group B fastener locations: 

Within 18 months after the effective date of 

this AD, replace all hi-lok Group B fasteners 

in accordance with Part 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2203, Revision 2, 

dated July 9, 2009. Repeat the inspection 

required by Part 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2203, Revision 2, dated July 9, 2009, 

at the applicable interval in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–54A2203, Revision 2, dated July 

9, 2009. 

Exceptions to Service Bulletin 

(k) Where Step 3 of Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2203, Revision 1, 

dated August 9, 2007; or Revision 2, dated 

July 9, 2009; provides the option to support 

the engine weight instead of removing the 

engine, this AD does not allow that option. 

This AD requires that the engine be removed 

before performing the inspections required 

by paragraph (h) of this AD. 

(l) Where Boeing Alert Service Bulletin 

747–54A2203, Revision 1, dated August 9, 

2007, specifies a compliance time after the 

date of that service bulletin, this AD requires 

compliance within the specified compliance 

time after October 9, 2007 (the effective date 

of AD 2007–19–19). 

(m) Where Boeing Alert Service Bulletin 

747–54A2203, Revision 2, dated July 9, 2009, 

specifies a compliance time after the date of 

Revision 1 or Revision 2 of that service 

bulletin, this AD requires compliance within 

the specified compliance time after the 

effective date of this AD. 

(n) Where Boeing Alert Service Bulletin 

747–54A2203, Revision 1, dated August 9, 

2007; or Boeing Alert Service Bulletin 747– 

54A2203, Revision 2, dated July 9, 2009; 

specifies to contact Boeing for appropriate 

action, this AD requires, before further flight, 

repair of the discrepancy or replacement of 

the discrepant part using a method approved 

in accordance with the Boeing Commercial 

Airplanes Organization Designation 

Authorization or in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

Credit for Actions Previously Accomplished 

(o) Actions performed before the effective 

date of this AD, in accordance with Boeing 

Alert Service Bulletin 747–53A2203, 

Revision 1, dated August 9, 2007, are 

acceptable for compliance with the 

corresponding actions specified in 

paragraphs (h), (i), and (j) of this AD. 

Alternative Methods of Compliance (AMOCs) 

(p)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Ken Paoletti, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6434; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 who 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 previously in 

accordance with AD 2007–19–19, 

Amendment 39–15210, are approved as 

AMOCs for the corresponding provisions of 

this AD. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 39189 

Issued in Renton, Washington, on June 25, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16606 Filed 7–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0674; Directorate 

Identifier 2010–NM–012–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Model 747 airplanes. This proposed AD 

would require repetitive inspections for 

cracking in the body skin around the aft 

corners of the nose wheel well; for 

certain airplanes, repetitive inspections 

for cracking in the skin splice plate at 

the aft corners of the nose wheel well; 

and related investigative and corrective 

actions if necessary. This proposed AD 

would also require repetitive postmodification inspections for cracking in 

the body skin and the skin splice plate; 

for certain airplanes, an inspection for 

steel cross-shaped doublers on the larger 

aluminum doublers; and corrective 

action if necessary. This proposed AD 

would also require repetitive surface 

high frequency eddy current (HFEC) 

inspections of a certain bulkhead outer 

chord, skin splice plate, and outer chord 

radius filler for cracking; repetitive 

detailed inspections for cracking of the 

bulkhead frame web and body skin; and 

corrective actions if necessary. This 

proposed AD would provide for 

optional terminating action for certain 

repetitive inspections. This proposed 

AD results from reports of cracking of 

the fuselage skin and adjacent internal 

skin splice plate at the left and right 

nose wheel well aft corners, and the 

outer chord of the body station (BS) 400 

bulkhead. We are proposing this AD to 

detect and correct cracking of the 

fuselage skin or splice plate, which, 

together with cracking of the bulkhead 

outer chord, could result in large skin 

cracks and subsequent in-flight rapid 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 23, 2010. 

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 20590, 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, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; 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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0674; Directorate Identifier 

2010–NM–012–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 have received reports of cracking 

of the fuselage skin and adjacent 

internal skin splice plate at the left and 

right nose wheel well aft corners, and 

the outer chord of the body station (BS) 

400 bulkhead. Cracks were found in the 

skin on an airplane that had 

accumulated about 6,355 total flight 

cycles. In addition, small cracks were 

found in the outer chord of the body 

station (BS) 400 bulkhead on airplanes 

that had accumulated fewer than 20,000 

total flight cycles. Cracking of the 

fuselage skin or splice plate, together 

with cracking of the bulkhead outer 

chord, if not detected and corrected, 

could result in large skin cracks and 

subsequent in-flight rapid 

decompression of the airplane. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2305, Revision 

2, dated January 15, 2009. The service 

bulletin describes procedures for 

repetitive external detailed inspections 

for cracking in the body skin around the 

aft corners of the nose wheel well; for 

certain airplanes, repetitive external 

detailed inspections for cracking in the 

skin splice plate at the aft corners of the 

nose wheel well, and modification of 

any cracked aft corners of the nose 

wheel well by installing modification 

doublers; and, for certain airplanes, and 

a one-time external general visual 

inspection for steel cross-shaped 

doublers. The modification, which, if 

accomplished to repair cracks or to 

eliminate the need for certain repetitive 

inspections, includes related 

investigative actions and corrective 

actions if necessary. The related 

investigative actions include an openhole HFEC inspection for cracking at 

fasteners common to the bulkhead outer 

chord, and a surface HFEC inspection or 

penetrant inspection for cracking of the 

skin if necessary. The corrective actions 

include repairing the crack, installing 

cross-shaped doublers, and contacting 

Boeing for repair instructions and doing 

the repair. 


srobinson on DSKHWCL6B1PROD with PROPOSALS