64520 Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 

inclusive, 1309 through 1312 inclusive, and 

1314; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by reports of 

cracks in the body station (BS) 1000 

bulkhead chord. We are issuing this AD to 

detect and correct fatigue cracks in the BS 

1000 bulkhead chord, which, if not repaired 

before they reach critical length, could result 

in the failure of the adjacent structure and 

skin and lead to in-flight depressurization of 

the airplane. 

Compliance 

(e) 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 Requirements of AD 90–09–

09

(f) For airplanes listed in Boeing Service 

Bulletin 747–53–2064, Revision 4, dated 

September 23, 1983, that have not been 

modified in accordance with Boeing Service 

Bulletin 747–53–2064, dated July 25, 1972: 

Within the next 1,000 landings after October 

15, 1984 (the effective date of AD 84–18–06, 

amendment 39–4912), or prior to the 

accumulation of 10,000 landings, whichever 

occurs later, and thereafter at intervals not to 

exceed 7,000 landings, conduct a high 

frequency eddy current (HFEC) inspection of 

the chord to detect cracks between stringers 

S–37 and S–39 at the chord radius, heel, and 

flanges adjacent to the fastener holes 

identified for inspection in Boeing Service 

Bulletin 747–53–2064, Revision 4, dated 

September 23, 1983. If cracks are found in 

the pressure bulkhead chord, accomplish the 

repair in accordance with the service bulletin 

before further flight. Repair of cracks along 

the chord radius under 5 inches in length, or 

across a chord flange that have not severed 

the chord flange, may be deferred 1,000 

landings by stop drilling and reinspecting for 

crack progression every 200 landings using 

HFEC. If crack progression is found, repair in 

accordance with the service bulletin prior to 

further flight. Inspections are to continue at 

intervals not to exceed 7,000 landings after 

repair. 

(g) For airplanes listed in Boeing Service 

Bulletin 747–53–2064, Revision 4, dated 

September 23, 1983, that have been modified 

in accordance with Boeing Service Bulletin 

747–53–2064, dated July 25, 1972: Within the 

next 1,000 landings after October 15, 1984, or 

prior to the accumulation of 10,000 landings 

after the modification, whichever is later, and 

thereafter at intervals not to exceed 10,000 

landings, conduct an HFEC inspection to 

detect cracks in the front spar pressure 

bulkhead lower chord heel from stringers S–

37 to S–39, and conduct an ultrasonic 

inspection to detect cracks in the fuselage 

skin originating at the indicated fastener 

holes beneath the forward drag splice fitting 

flanges, in accordance with the service 

bulletin. If any cracks are found, repair in 

accordance with Boeing Service Bulletin 

747–53–2064, Revision 4, dated September 

23, 1983, before further flight. Inspections are 

to continue at intervals not to exceed 10,000 

landings after repair.

New Requirements of This AD 

Initial Inspections 

(h) At the later of the times specified in 

paragraph (h)(1), (h)(2), or (h)(3) of this AD: 

Except as provided by paragraph (i) of this 

AD, perform an HFEC inspection of BS 1000 

bulkhead chord for cracks, a detailed 

inspection of the bathtub fittings, if installed, 

for cracks, and corrective action, as 

applicable, by accomplishing all the actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2471, dated March 27, 2003. Any 

applicable corrective action must be done 

before further flight. Accomplishment of the 

HFEC and detailed inspections required by 

paragraph (h) of this AD ends the 

requirements of paragraphs (f) and (g) of this 

AD.

Note 1: For the purposes of this AD, a 

detailed inspection is ‘‘an intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirrors, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(1) Prior to the accumulation of 10,000 

total flight cycles. 

(2) Within 18 months after the effective 

date of this AD. 

(3) For airplanes on which the repair (i.e., 

chord replacement) has been accomplished 

in accordance with Boeing Service Bulletin 

747–53–2362, dated March 26, 1992, or in 

accordance with paragraph (f) or (g) of this 

AD (i.e., per Boeing Service Bulletin 747–53–

2064, Revision 4, dated September 23, 1983): 

Within 3,000 flight cycles after the 

replacement was accomplished.

Note 2: Repairs (i.e., chord replacement) 

accomplished prior to the effective date of 

this AD in accordance with Boeing Service 

Bulletin 747–53–2064, Revision 1, dated May 

18, 1973; Revision 2, dated February 22, 

1974; Revision 3, dated September 13, 1974; 

Revision 5, dated July 23, 1987; or Revision 

6, dated June 22, 1989; are considered to be 

applicable to the inspection threshold 

specified in paragraph (h)(3) of this AD.

(i) If any crack is found during any 

inspection required by paragraph (h) of this 

AD, and Boeing Alert Service Bulletin 747–

53A2471, dated March 27, 2003, specifies 

contacting Boeing for additional information: 

Before further flight, repair per a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA. For a repair 

method to be approved by the Manager, 

Seattle ACO, as required by this paragraph, 

the Manager’s approval letter must 

specifically refer to this AD. 

Repetitive Inspections 

(j) Except as provided by paragraph (k) of 

this AD, repeat the inspections required by 

paragraph (h) of this AD thereafter at 

intervals not to exceed 3,000 flight cycles. 

(k) For airplanes on which both the chord 

replacement and bathtub fitting replacement 

were done in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2471, dated March 

27, 2003: Repeat the inspections required by 

paragraph (h) of this AD within 6,000 flight 

cycles after accomplishing both 

replacements. Thereafter repeat the 

inspections at intervals not to exceed 3,000 

flight cycles. 

Alternative Methods of Compliance (AMOC) 

(l)(1) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

AMOCs for this AD. 

(2) AMOCs, approved previously in 

accordance with AD 90–09–09, amendment 

39–6586, are approved as AMOCs with 

paragraph (f) or (g) of this AD, as applicable.

Issued in Renton, Washington, on October 

26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24726 Filed 11–4–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19537; Directorate 

Identifier 2004–NM–145–AD] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

Series Airplanes; and C4–605R Variant 

F Airplanes (Collectively Called A300–

600), and Model A310 Series Airplanes 

Equipped With Certain Honeywell 

Inertial Reference Units (IRU)

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes; and C4–

605R Variant F airplanes (collectively 

called A300–600), and Model A310 

series airplanes, equipped with certain 

Honeywell inertial reference units 

(IRUs). This proposed AD would require 

revising the Limitations section of the 

Airplane Flight Manual to prohibit the 

use of CAT 2 and CAT 3 automatic 

landing and rollout procedures at 

certain airports. This proposed AD is 

prompted by a report that some 

magnetic deviation tables in the IRU 

database are obsolete and contain 

significant differences with the real 

magnetic deviations. We are proposing 

this AD to prevent an airplane from 

deviating from the runway centerline, 

and possibly departing the runway.

Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 64521

DATES: We must receive comments on 

this proposed AD by December 6, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket web site: Go to

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• By fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Technical information: Dan Rodina, 

Aerospace Engineer, International 

Branch, ANM–116, FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19537; Directorate Identifier 

2004–NM–145–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments submitted by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of our docket 

website, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You can 

review the DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you can visit http://

dms.dot.gov. 

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http://

www.plainlanguage.gov. 

Examining the Docket 

You can examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

Discussion 

The Direction Generale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on certain Airbus Model A300 B4–

600, B4–600R, and F4–600R series 

airplanes; and C4–605R Variant F 

airplanes (collectively called A300–

600), and Model A310 series airplanes, 

equipped with certain Honeywell 

inertial reference units (IRUs). The 

DGAC advises that the magnetic 

variation table, which is implemented 

in certain Honeywell IRUs, is obsolete 

in certain airports. Studies have shown 

that for a given airport, a difference 

greater than two degrees between the 

real magnetic deviation and the one 

implemented in the IRUs could lead to 

an unsafe situation during CAT 2 or 

CAT 3 automatic landings and rollouts. 

This condition, if not corrected, could 

result in the airplane deviating from the 

runway centerline and possibly 

departing the runway. 

Relevant Service Information 

Airbus has issued Temporary 

Revisions (TRs) 6.01.03/08 (for Model 

A300–600 series airplanes) and 6.01.03/

36 (for Model A310 series airplanes), 

both dated January 6, 2003. The TRs 

give a list of airports concerned and a 

date from which automatic landings 

(AUTOLAND) and automatic taxiing 

after touchdown (rollout) procedures are 

prohibited. The DGAC mandated the 

service information and issued French 

airworthiness directive F–2004–093, 

issued June 23, 2004, to ensure the 

continued airworthiness of these 

airplanes in France. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of § 21.29 of 

the Federal Aviation Regulations (14 

CFR 21.29) and the applicable bilateral 

airworthiness agreement. Pursuant to 

this bilateral airworthiness agreement, 

the DGAC has kept the FAA informed 

of the situation described above. We 

have examined the DGAC’s findings, 

evaluated all pertinent information, and 

determined that we need to issue an AD 

for products of this type design that are 

certificated for operation in the United 

States. 

Therefore, we are proposing this AD, 

which would require revising the 

Limitations section of the airplane flight 

manual (AFM) to prohibit the use of 

CAT 2 and CAT 3 automatic landing 

and rollout procedures at certain 

airports. The proposed AD would 

require you to use the service 

information described previously to 

perform these actions. After 

accomplishing the replacement of the 

Honeywell IRU required by AD 2003–

20–01, amendment 39–13319 (68 FR 

55814, September 29, 2003), the AFM 

revision may be removed. 

Costs of Compliance 

This proposed AD would affect about 

136 airplanes of U.S. registry. The 

proposed AFM revision would take 

64522 Federal Register / Vol. 69, No. 214 / Friday, November 5, 2004 / Proposed Rules 

about 1 work hour per airplane, at an 

average labor rate of $65 per work hour. 

Based on these figures, the estimated 

cost of the proposed AD for U.S. 

operators is $8,840, or $65 per airplane.

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. 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.

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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

Airbus: Docket No. FAA–2004–19537; 

Directorate Identifier 2004–NM–145–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

December 6, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus airplanes, 

certificated in any category; as listed in Table 

1:

TABLE 1.—APPLICABILITY

Model— Equipped with any Honeywell airplanes inertial 

reference unit (IRU) having part number—

Excluding airplanes modified in accordance 

with—

A300 B4–600, B4–600R, and F4–600R series 

airplanes; and C4–605R Variant F airplanes 

(collectively called A300–600).

HG1050BD01, HG1050BD02, or 

HG1050BD05.

Airbus modification 12304 in production. 

A310 series airplanes ........................................ HG1050BD01, HG1050BD02, or 

HG1050BD05.

Airbus modification in production. 

Unsafe Condition 

(d) This AD was prompted by a report that 

some magnetic deviation tables in the IRU 

database are obsolete and contain significant 

differences with the real magnetic deviations. 

We are issuing this AD to prevent an airplane 

from deviating from the runway centerline, 

and possibly departing the runway. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Airplane Flight Manual (AFM) Revision 

(f) Within 10 days after the effective date 

of this AD, revise the Limitations section of 

the AFM by inserting a copy of the applicable 

Airbus Airplane Flight Manual Temporary 

Revision listed in Table 2 of this AD into the 

AFM.

Note 1: When Airbus includes these TRs in 

general revisions of the AFM, the general 

revisions may be inserted in the AFM, 

provided the relevant information in the 

general revision is identical to that in TRs 

6.01.03/08 and 6.01.03/36.

TABLE 2.—AFM TRS

Model— Airbus— Dated—

(1) A300 B4–600, B4–600R, and F4–600R series airplanes; and C4–605R Variant F airplanes (collectively called A300–600).A300–600 Flight Manual TR 6.01.03/08 .......... February 9, 2003. 

(2) A310 series airplanes .................................. A310 Flight Manual TR6.01.03/36 ................... February 9, 2003. 

Terminating Action 

(g) After replacing the Honeywell inertial 

reference units (IRUs) with new or modified 

Honeywell IRUs in accordance with the 

requirements of AD 2003–20–01, amendment 

39–13319 (68 FR 55814), the AFM revision 

required by paragraph (f) of this AD may be 

removed. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(i) French airworthiness directive F–2004–

093 (B), issued June 23, 2004, also addresses 

the subject of this AD.

Issued in Renton, Washington, on October 

28, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24725 Filed 11–4–04; 8:45 am] 

BILLING CODE 4910–13–P