Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5765

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–107–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to all 

Model 747 series airplanes. This 

proposal would require a repetitive 

detailed inspection of the aft pressure 

bulkhead for indications of ‘‘oil cans’’

and previous ‘‘oil can’’ repairs, and 

corrective actions, if necessary. An ‘‘oil 

can’’ is an area on a pressure dome web 

that moves when pushed from the 

forward side. This action is necessary to 

detect and correct the propagation of 

fatigue cracks in the vicinity of ‘‘oil 

cans’’ on the web of the aft pressure 

bulkhead, which could result in rapid 

decompression and overpressurization 

of the tail section, and consequent loss 

of control of the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Comments must be received by 

March 22, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

107–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–107–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Boeing Commercial Airplanes, PO Box 

3707, Seattle, Washington 98124–2207. 

This information may be examined at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Nicholas Kusz, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6432; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION:

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2003–NM–107–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2003–NM–107–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The FAA has received a report 

indicating that a 2.1-inch long crack in 

the web of the aft pressure bulkhead at 

the perimeter of an ‘‘oil can’’ was found 

on a Model 747SR series airplane. An 

‘‘oil can’’ is an area on a pressure dome 

web that moves when pushed from the 

forward side. The cause of the crack is 

fatigue. This condition, if not detected 

and corrected, could result in the 

propagation of fatigue cracks in the 

vicinity of ‘‘oil cans’’ on the web of the 

aft pressure bulkhead, which could 

result in rapid decompression and 

overpressurization of the tail section, 

and consequent loss of control of the 

airplane. 

The subject area on Model 747SR 

series airplanes is almost identical to 

that on Model 747–100, –200B, –200F, 

–200C, –100B, –300, –100B–SUD, –400, 

–400D, and –400F series airplanes; and 

Model 747SP series airplanes. 

Therefore, those airplanes may be 

subject to the unsafe condition revealed 

on the Model 747SR series airplanes.

Explanation of Relevant Service 

Information 

The FAA has reviewed and approved 

Boeing Alert Service Bulletin 747–

53A2482, dated October 3, 2002, which 

describes procedures for performing a 

repetitive detailed inspection of the aft 

pressure bulkhead for indications of ‘‘oil 

cans’’ and previous ‘‘oil can’’ repairs, 

and corrective actions, if necessary. The 

corrective actions include performing a 

repetitive eddy current inspection of the 

web around the periphery of the ‘‘oil 

can’’ for cracks, and repair if necessary; 

and performing a detailed inspection of 

the web around previous ‘‘oil can’’

repairs for cracks. Repair of all ‘‘oil 

cans’’ eliminates the need for the 

repetitive eddy current inspection of 

existing ‘‘oil cans.’’ Accomplishment of 

the actions specified in the service 

bulletin is intended to adequately 

address the identified unsafe condition. 

Explanation of Requirements of 

Proposed Rule 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other products of this same 

type design, the proposed AD would 

require accomplishment of the actions 

specified in the service bulletin 

described previously, except as 

discussed below. 

Differences Between Proposed Rule and 

Service Bulletin 

Operators should note that when a 

previous ‘‘oil can’’ repair is found, 

section 3.B.9.a. of the service bulletin 

states that if no cracking is found, no 

5766 Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 

action on the repaired area is required 

at this time, and that the repetitive 

inspections of the aft pressure bulkhead 

for ‘‘oil cans’’ at 2,000 flight cycle 

intervals are to continue. The FAA has 

determined, however, that the actions 

specified in the service bulletin for ‘‘oil 

cans’’ found at previous ‘‘oil can’’

repairs are insufficient. It is possible 

that the ‘‘oil can’’ that was originally 

repaired within the allowable limits of 

the service bulletin has since grown to 

exceed the allowable limits. In 

accordance with Figure 4 or Figure 5 of 

the service bulletin, this proposed AD 

would require an eddy current 

inspection for cracks if ‘‘oil cans’’ are 

found at previous ‘‘oil can’’ repairs. In 

addition, if no cracking is found, this 

proposed AD would require verification 

that any ‘‘oil cans’’ at previous ‘‘oil can’’

repairs are within the allowable limits 

of the service bulletin. For any ‘‘oil can’’

that meets the allowable limits, this 

proposed AD would require repetitive 

eddy current inspections at intervals not 

to exceed 1,000 flight cycles until a 

repair that terminates the ‘‘oil can’’ is 

completed. For any ‘‘oil can’’ that does 

not meet the allowable limits, this 

proposed AD would require repair of 

the ‘‘oil can’’ and, if any ‘‘oil can’’

remains after the repair, this proposed 

AD would require repetitive eddy 

current inspections at intervals not to 

exceed 1,000 flight cycles. 

Operators should also note that, 

although the service bulletin specifies 

that the manufacturer may be contacted 

for disposition of certain repair 

conditions, this proposed AD would 

require the repair of those conditions to 

be accomplished per a method approved 

by the FAA, or per data meeting the 

type certification basis of the airplane 

approved by a Boeing Company 

Designated Engineering Representative 

who has been authorized by the FAA to 

make such findings. 

Cost Impact 

There are approximately 1,140 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

254 airplanes of U.S. registry would be 

affected by this proposed AD, that it 

would take approximately 6 work hours 

per airplane to accomplish the proposed 

inspections, and that the average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of the 

proposed AD on U.S. operators is 

estimated to be $99,060, or $390 per 

airplane, per inspection cycle. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the proposed requirements of this AD 

action, and that no operator would 

accomplish those actions in the future if 

this proposed AD were not adopted. The 

cost impact figures discussed in AD 

rulemaking actions represent only the 

time necessary to perform the specific 

actions actually required by the AD. 

These figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations proposed herein 

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. Therefore, 

it is determined that this proposal 

would not have federalism implications 

under Executive Order 13132. 

For the reasons discussed above, I 

certify that this proposed regulation (1) 

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not 

a ‘‘significant rule’’ under the DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979); and (3) if 

promulgated, 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. A copy of the draft 

regulatory evaluation prepared for this 

action is contained in the Rules Docket. 

A copy of it may be obtained by 

contacting the Rules Docket at the 

location provided under the caption 

ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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. Section 39.13 is amended by 

adding the following new airworthiness 

directive:

Boeing: Docket 2003–NM–107–AD.

Applicability: All Model 747 series 

airplanes; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously.

Note 1: This AD refers to certain portions 

of a Boeing service bulletin for inspections 

and repair information. In addition, this AD 

specifies requirements beyond those 

included in the service bulletin. Where the 

AD and the service bulletin differ, the AD 

prevails.

To detect and correct the propagation of 

fatigue cracks in the vicinity of ‘‘oil cans’’ on 

the web of the aft pressure bulkhead, which 

could result in rapid decompression and 

overpressurization of the tail section, and 

consequent loss of control of the airplane, 

accomplish the following: 

Service Bulletin References 

(a) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2482, dated October 3, 2002. 

Initial and Repetitive Inspections 

(b) Prior to the accumulation of 30,000 

flight cycles, or within 1,000 flight cycles 

after the effective date of this AD, whichever 

is later, perform a detailed inspection of the 

aft pressure bulkhead for indications of ‘‘oil 

cans’’ and previous ‘‘oil can’’ repairs, in 

accordance with the service bulletin.

Note 2: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

(c) If no indication of an ‘‘oil can’’ is found 

and no indication of a previous ‘‘oil can’’

repair is found, during the detailed 

inspection required by paragraph (b) of this 

AD, repeat the detailed inspection thereafter 

at intervals not to exceed 2,000 flight cycles. 

Indication of ‘‘Oil Can’’

(d) If any indication of an ‘‘oil can’’ is 

found during the detailed inspection 

required by paragraph (b) or (c) of this AD, 

before further flight, perform an eddy current 

inspection of the web around the periphery 

of the ‘‘oil can’’ indication for cracks, as 

shown in Figure 3 of the service bulletin. 

(e) If no crack is found during the eddy 

current inspection required by paragraphs (d) 

and (f)(2) of this AD, do the actions specified 

in paragraph (e)(1) or (e)(2) of this AD, as 

applicable. 

(1) For the ‘‘oil can’’ that meets the 

allowable limits specified in the service 

bulletin: Repeat the eddy current inspection 

specified in paragraph (d) of this AD 

thereafter at intervals not to exceed 1,000 

flight cycles. As an option, repair the ‘‘oil 

can’’ in accordance with paragraph (e)(2) of 

this AD. 

(2) For the ‘‘oil can’’ that does not meet the 

allowable limits specified in the service 

bulletin: Before further flight, repair the ‘‘oil 

can’’ in accordance with the service bulletin. 

If the repair eliminates the ‘‘oil can,’’

accomplishment of this repair constitutes a 

terminating action for the repetitive eddy 

Federal Register / Vol. 69, No. 25 / Friday, February 6, 2004 / Proposed Rules 5767

current inspection requirements of paragraph 

(e)(1) of this AD for this location only. 

However, the repetitive detailed inspection 

required by paragraph (c) of this AD is still 

required. If any ‘‘oil can’’ remains after the 

repair, repeat the eddy current inspection 

thereafter at intervals not to exceed 1,000 

flight cycles. 

Indication of Previous ‘‘Oil Can’’ Repairs 

(f) If any previous ‘‘oil can’’ repair is found 

during the detailed inspection required by 

paragraph (b) or (c) of this AD, before further 

flight, do a detailed inspection of the web for 

cracks and ‘‘oil cans,’’ as shown in Figure 4 

or Figure 5 of the service bulletin, as 

applicable. 

(1) If no crack and no ‘‘oil can’’ are found, 

repeat the detailed inspection in accordance 

with paragraph (c) of this AD. 

(2) If any ‘‘oil can’’ is found, before further 

flight, do the eddy current inspection for 

cracks as shown in Figure 3 of the service 

bulletin. 

(3) If no crack is found during the eddy 

current inspection required by paragraph 

(f)(2) of this AD, do the actions specified in 

paragraph (e)(1) or (e)(2) of this AD, as 

applicable. 

Repair of Cracks 

(g) If any crack is found during any 

inspection required by this AD, before further 

flight, repair in accordance with the service 

bulletin. If cracks or damage exceeds limits 

specified in the service bulletin and the 

service bulletin specifies to contact Boeing 

for appropriate action: Before further flight, 

repair per a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA; or per data meeting the type 

certification basis of the airplane approved 

by a Boeing Company Designated 

Engineering Representative who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved, the approval must specifically 

reference this AD. 

Alternative Methods of Compliance 

(h) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

for this AD.

Issued in Renton, Washington, on January 

29, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–2469 Filed 2–5–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–227–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Fan Jet Falcon Series Airplanes 

and Model Mystere-Falcon 20 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes the 

adoption of a new airworthiness 

directive (AD) that is applicable to 

certain Dassault Model Fan Jet Falcon 

series airplanes and Model MystereFalcon 20 series airplanes. This 

proposal would require inspecting and 

testing for fatigue cracking due to stress 

corrosion in the vertical posts of the 

window frames in the flight 

compartment. This action is necessary 

to prevent fatigue cracking of the 

window frames, which could result in 

rapid depressurization of the fuselage 

and consequent reduced structural 

integrity of the airplane. This action is 

intended to address the identified 

unsafe condition.

DATES: Comments must be received by 

March 8, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2002–NM–

227–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2002–NM–227–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Dassault Falcon Jet, P.O. Box 2000, 

South Hackensack, New Jersey 07606. 

This information may be examined at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2002–NM–227–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2002–NM–227–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the