49366 Federal Register / Vol. 73, No. 163 / Thursday, August 21, 2008 / Proposed Rules 

the instructions of paragraphs 2.C.(1) through 

2.C.(3), and paragraphs 2.D.(1) through 

2.D.(3), of the Accomplishment Instructions 

of BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–194, 

dated January 10, 2007, except as required by 

paragraphs (f)(2), (f)(3), and (f)(4) of this AD. 

(2) If any defect is found during the 

inspection specified in paragraph (f)(1) of 

this AD, before further flight, replace the 

affected bolts in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–194, dated January 

10, 2007, except as required by paragraph 

(f)(3) and (f)(4) of this AD. 

(3) For airplanes on which replacement 

parts are not available during the 

replacement specified in paragraph (f)(2) of 

this AD, do the actions in paragraphs (f)(3)(i) 

and (f)(3)(ii) of this AD in accordance with 

the Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–194, dated January 

10, 2007. 

(i) Before further flight, temporarily 

reinstall removed oversized bolts, provided 

the bolts are serviceable. 

(ii) Within 2,000 flight cycles after doing 

the inspection required by paragraph (f)(1) of 

this AD, replace all temporary oversized bolts 

that were installed in accordance with 

paragraph (f)(3)(i) of this AD. 

(4) Where BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53–

194, dated January 10, 2007, specifies to 

contact BAE Systems (Operations) Limited if 

any defect is found in the second oversize 

fastener bore, before further flight, contact 

BAE Systems (Operations) Limited for repair 

instructions and do the repair. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2007–

0277, dated November 5, 2007, and BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–194, dated January 

10, 2007, for related information. 

Issued in Renton, Washington, on August 

6, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19364 Filed 8–20–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0898; Directorate 

Identifier 2007–NM–200–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200 and 767–300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 767–200 and 767–

300 series airplanes. This proposed AD 

would require detailed inspections of 

the aft pressure bulkhead for damage, 

mid-frequency eddy current (MFEC) and 

low frequency eddy current (LFEC) 

inspections of radial web lap splices, 

tear strap splices, and super tear strap 

splices for cracking, and corrective 

actions if necessary. This AD results 

from analysis that indicates fatigue 

cracks of the web lap splice, tear strap 

splice, or super tear strap splice of the 

aft bulkhead are expected to occur on 

certain Boeing Model 767–200 and 767–

300 series airplanes. We are proposing 

this AD to detect and correct fatigue 

cracks of the aft pressure bulkhead, 

which could result in rapid 

decompression of the passenger 

compartment and possible damage or 

interference with airplane control 

systems that penetrate the bulkhead, 

and consequent loss of controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by October 6, 2008. 

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 AD, contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

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: 

Tamara L. Anderson, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6421; 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–2008–0898; Directorate Identifier 

2007–NM–200–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 


sroberts on PROD1PC70 with PROPOSALS
Federal Register / Vol. 73, No. 163 / Thursday, August 21, 2008 / Proposed Rules 49367 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have previously issued AD 2005–

03–11, amendment 39–13967 (70 FR 

7174, February 11, 2005). (A correction 

of the rule was published in the Federal 

Register on March 11, 2005 (70 FR 

12119, March 11, 2005).) That AD 

applies to certain Boeing Model 767–

200 and 767–300 series airplanes, line 

numbers 1 through 175 inclusive. That 

AD was prompted by a report of 

multiple-site fatigue cracking (multiplesite damage) in two lap splices on the 

aft pressure bulkhead of one airplane. 

That AD currently requires repetitive 

detailed and eddy current inspections of 

the aft pressure bulkhead for damage 

and cracking, one-time detailed and 

high frequency eddy current inspections 

of any ‘‘oil can’’ located on the aft 

pressure bulkhead for damage and 

cracking, and related corrective actions 

if necessary. 

Since the issuance of that AD, 

analysis indicates that fatigue cracks of 

the web lap splice, tear strap splice, or 

super tear strap splice of the aft 

bulkhead are expected to occur on 

Boeing Model 767–200 and 767–300 

series airplanes having line numbers 

176 through 423 inclusive that have 

accumulated 35,000 or more total flight 

cycles. There have been no reports of 

such fatigue cracks on these in-service 

airplanes. Such fatigue cracking, if not 

corrected, could result in rapid 

decompression of the passenger 

compartment and possible damage or 

interference with airplane control 

systems that penetrate the bulkhead, 

and consequent loss of controllability of 

the airplane. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–53A0147, dated 

August 16, 2007. The service bulletin 

describes procedures for: 

• Doing an initial detailed inspection 

of the aft pressure bulkhead for damage 

such as dents, punctures, nicks, gouges, 

cracks, corrosion, and scratches, and 

repeating those inspections. 

• Doing initial mid-frequency eddy 

current (MFEC) and low-frequency eddy 

current (LFEC) inspections of the radial 

web lap splices, tear strap splices, and 

super tear strap splices for cracking, and 

repeating those inspections. 

• Contacting Boeing for inspection 

instructions where inspection is 

prevented by a repair common to the 

inspection area. 

• Doing applicable corrective actions, 

which include repairing any damage 

that exceeds certain allowable limits, 

and contacting Boeing for repair 

instructions. The service bulletin 

specifies the following compliance 

times: 

• For the initial inspections: 35,000 

total flight-cycles, or 18 months or 3,000 

flight-cycles after the date of the service 

bulletin, whichever occurs first. 

• For the repetitive inspections: 

Within 3,000 flight-cycles of the initial 

inspection, and thereafter at intervals 

not to exceed 3,000 flight-cycles. 

• For the applicable corrective 

actions: Before further flight. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other airplanes of this same 

type design. For this reason, we are 

proposing this AD, which would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between Proposed Rule 

and Service Bulletin.’’

Differences Between Proposed Rule and 

Service Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair and 

inspect certain conditions, but this 

proposed AD would require repairing 

and inspecting 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 an 

Authorized Representative for the 

Boeing Commercial Airplanes 

Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Clarification of Repetitive Inspections 

Specified in Service Bulletin 

The Accomplishment Instructions of 

the service bulletin specifies to only 

repeat the inspections if no crack is 

found. However, Table 2 of paragraph 

1.E, ‘‘Compliance,’’ of the service 

bulletin identifies repeat intervals for 

the inspections, regardless of inspection 

findings. The intent is that the 

inspections be repeated for all findings. 

Therefore, this proposed AD would 

require repetitive inspections at the 

applicable repeat intervals listed in 

Table 2 of paragraph 1.E., 

‘‘Compliance.’’

Costs of Compliance 

There are about 244 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 84 

airplanes of U.S. registry. The proposed 

actions would take about 31 work hours 

per airplane, at an average labor rate of 

$80 per work hour. Based on these 

figures, the estimated cost of the 

proposed AD for U.S. operators is 

$208,320, or $2,480 per airplane, per 

inspection cycle. 

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, Safety. 


sroberts on PROD1PC70 with PROPOSALS
49368 Federal Register / Vol. 73, No. 163 / Thursday, August 21, 2008 / Proposed Rules 

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: 

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

§ 39.13 [Amended] 

2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Boeing: Docket No. FAA–2008–0898; 

Directorate Identifier 2007–NM–200–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 6, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 767–

200 and 767–300 series airplanes, certificated 

in any category; as identified in Boeing Alert 

Service Bulletin 767–53A0147, dated August 

16, 2007. 

Unsafe Condition 

(d) This AD results from analysis that 

indicates fatigue cracks of the web lap splice, 

tear strap splice, or super tear strap splice of 

the aft bulkhead are expected to occur on 

certain Boeing Model 767–200 and 767–300 

series airplanes. We are proposing this AD to 

detect and correct fatigue cracks of the aft 

pressure bulkhead, which could result in 

rapid decompression of the passenger 

compartment and possible damage or 

interference with airplane control systems 

that penetrate the bulkhead, and consequent 

loss of controllability of the airplane. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspections and Applicable Related 

Investigative and Corrective Actions 

(f) Except as provided by paragraphs (f)(1) 

and (f)(2) of this AD: At the applicable 

compliance time and repeat intervals listed 

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

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 767–53A0147, dated August 16, 

2007, do detailed inspections of the aft 

pressure bulkhead for damage, midfrequency eddy current (MFEC) and lowfrequency eddy current (LFEC) inspections of 

radial web lap splices, tear strap splices, and 

super tear strap splices for cracking and 

applicable corrective actions by 

accomplishing all the applicable actions 

specified in the Accomplishment 

Instructions of the service bulletin. 

(1) Where Table 1 of paragraph 1.E., 

‘‘Compliance,’’ of the service bulletin 

specifies a compliance time after the date on 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where the service bulletin specifies a 

compliance time of ‘‘As given by Boeing’’ or 

to contact Boeing for the appropriate action, 

this AD requires, before further flight, 

inspections of the area of repair and repair 

of any damaged/cracked part, as applicable, 

using a method approved in accordance with 

the procedures specified in paragraph (g) of 

this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Tamara L. Anderson, Aerospace Engineer, 

Airframe Branch, ANM–120S, 1601 Lind 

Avenue, SW., Renton, Washington, telephone 

(425) 917–6421; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization 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. 

Issued in Renton, Washington, on August 

8, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19363 Filed 8–20–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0899; Directorate 

Identifier 2008–NM–022–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

Flight Management Systems (FMSs) 

Equipped with Honeywell NZ–2000 

Navigation Computers and Honeywell 

IC–800 or IC–800E Integrated Avionics 

Computers; as Installed on Various 

Transport Category Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all 

Honeywell FMSs served by Honeywell 

NZ–2000 navigation computers and IC–

800 integrated avionics computers. The 

existing AD currently requires 

identifying affected computers by part 

number and software modification level 

and revising the Limitations section of 

applicable airplane flight manuals to 

provide procedures for retaining 

optimum position determination and 

intended navigation. This proposed AD 

would require uploading new software, 

which would terminate the existing 

requirements. This proposed AD results 

from reports of in-flight unannunciated 

shifts of computed position in airplanes 

with the subject FMS computers. We are 

proposing this AD to prevent a shift in 

the FMS computed position, which 

could result in uncommanded 

deviations from the intended flight path 

of the airplane and, if those deviations 

are undetected by the flight crew, 

compromised terrain/traffic avoidance. 

DATES: We must receive comments on 

this proposed AD by October 6, 2008. 

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. 


sroberts on PROD1PC70 with PROPOSALS