Federal Register / Vol. 61, No. 173 / Thursday, September 5, 1996 / Rules and Regulations 46703

published at 61 FR 17551 on April 22,

1996, is adopted as a final rule without

change.

Dated: August 29, 1996.

Terry L. Medley,

Acting Assistant Secretary, Marketing and

Regulatory Programs.

[FR Doc. 96–22661 Filed 9–04–96; 8:45 am]

BILLING CODE 3410–02–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–249–AD; Amendment

39–9730; AD 96–18–06]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–111, –211, and –231 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320–111, –211, and –231 series

airplanes, that requires visual

inspections to detect cracks of the

fittings of the pressurized floor at frame

36, and renewal of the zone protective

finish or replacement of fittings with

new fittings, if necessary. This

amendment is prompted by a report of

fatigue cracking found on the

pressurized floor fitting at frame 36

under the lower surface panel. The

actions specified by this AD are

intended to prevent such fatigue

cracking, which could result in failure

of a floor fitting and subsequent

depressurization of the fuselage.

DATES: Effective October 10, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of October 10,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A320–111, –211, and –231 series

airplanes was published in the Federal

Register on April 19, 1996 (61 FR

17257). That action proposed to require

visual inspection(s) to detect cracks of

the six fittings of the pressurized floor

at frame 36 under the lower surface

panel, and renewing the zone protective

finish or replacement of the fittings with

new fittings, if necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Both commenters support the

proposed rule.

New Service Information

Airbus has issued Revision 1 of

Service Bulletin A320–57–1028, dated

April 19, 1996. This revision is

essentially identical in its technical

content as the original version, which

was cited in the proposal as the

appropriate source of service

information. The Direction Ge ́ne ́rale de

l’Aviation Civile (DGAC), which is the

airworthiness authority for France, has

classified this revised service bulletin as

mandatory. Accordingly, this final rule

has been revised to reference Revision 1

of the service bulletin. It has also been

revised to note that any of the required

actions that were performed in

accordance with the originally issued

service bulletin prior to the effective

date of the final rule are considered

acceptable for compliance with this AD.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 22 Airbus

Model A320–111, –211, and –231 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 3 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $3,960,

or $180 per airplane, per inspection

cycle.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); 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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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.
46704 Federal Register / Vol. 61, No. 173 / Thursday, September 5, 1996 / Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–18–06 Airbus Industrie: Amendment 39–

9730. Docket 95–NM–249–AD.

Applicability: Model A320–111, –211, and

–231 series airplanes; manufacturer’s serial

numbers 002 through 008 inclusive, 010

through 014 inclusive, 016 through 078

inclusive, and 080 through 104 inclusive; on

which Airbus Modification 21282P01497

(reference Airbus Service Bulletin A320–57–

1029) has not been installed; certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For airplanes that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking on the

pressurized floor fitting at frame 36 under the

lower surface panel, which could result in

failure of a fitting and subsequent

depressurization of the fuselage, accomplish

the following:

Note 2: Inspections and replacement(s) that

were performed prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A320–57–1028, dated April 12,

1996, are considered acceptable for

compliance with this AD.

(a) Prior to the accumulation of 16,000 total

landings, or within 6 months after the

effective date of this AD, whichever occurs

later, perform a visual inspection to detect

cracks of the 6 fittings of the pressurized

floor at frame 36 under the lower surface

panel, in accordance with Airbus Service

Bulletin A320–57–1028, Revision 1, dated

April 19, 1996.

(1) If no cracking is found, prior to further

flight, renew the zone protective finish in

accordance with the service bulletin. Repeat

the visual inspection thereafter at intervals

not to exceed 12,000 landings.

(2) If only 1 of the 6 fittings is found to be

cracked and that crack is less than or equal

to 0.59 inch (15 mm) in length, prior to

further flight, replace the cracked fitting with

a new fitting in accordance with the service

bulletin. Thereafter, prior to the

accumulation of 500 landings following

accomplishment of this replacement, replace

the remaining 5 fittings with new fittings in

accordance with the service bulletin.

(3) If only 1 of the 6 fittings is found to be

cracked and that crack is greater than 0.59

inch (15 mm) in length, prior to further flight,

replace all six fittings with new fittings in

accordance with the service bulletin.

(4) If 2 or more fittings are found to be

cracked, prior to further flight, replace all 6

fittings with new fittings in accordance with

the service bulletin.

(b) Replacement of all 6 fittings with new

fittings in accordance with Airbus Service

Bulletin A320–57–1028, Revision 1, dated

April 19, 1996, constitutes terminating action

for the inspection requirements of this AD.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(d) The actions shall be done in accordance

with Airbus Service Bulletin A320–57–1028,

Revision 1, dated April 19, 1996, which

contains the following list of effective pages:

Page number

Revision

level

shown on

page

Date shown on

page

1–3 ............... 1 .............. Apr. 19, 1996.

4–15 ............. Original .... Aug. 12, 1991.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

October 10, 1996.

Issued in Renton, Washington, on August

23, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–22144 Filed 9–4–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–204–AD; Amendment

39–9735; AD 96–18–11]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–10–10 and –15

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–10–10 and –15

series airplanes, that requires repetitive

inspections to detect cracks in the

bulkhead tee caps, and repair and

follow-on actions, if necessary. It also

provides for an optional terminating

modification for the repetitive

inspections. This amendment is

prompted by reports of cracking in the

bulkhead tee caps at a fuselage station

in the area of certain longerons due to

fatigue. The actions specified by this AD

are intended to prevent such fatigue

cracking, which could result in loss of

pressurization and damage to adjacent

structure.

DATES: Effective October 10, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of October 10,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from McDonnell Douglas Corporation,

3855 Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Department C1–L51 (2–60). This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA, Los

Angeles Aircraft Certification Office,

Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Maureen Moreland, Aerospace

Engineer, Airframe Branch, ANM–120L,

FAA, Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California 90712; telephone

(310) 627–5238; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain McDonnell

Douglas Model DC–10–10 and –15

series airplanes was published in the

Federal Register on March 28, 1995 (61

FR 13787). That action proposed to

require repetitive inspections to detect

cracks in the bulkhead tee caps, and

repair and follow-on actions, if

necessary. The proposal would also

provide for an optional terminating

modification for the repetitive

inspections.

Interested persons have been afforded

an opportunity to participate in the