8872 Federal Register / Vol. 62, No. 39 / Thursday, February 27, 1997 / Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–11–AD; Amendment

39–9948; AD 97–05–04]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A320–111, –211, and –231 series

airplanes, that currently requires

replacing the existing standby generator

control unit (GCU) with a new improved

standby GCU. That action was prompted

by reports of improper functioning of

the standby GCU. This amendment

requires replacement of the GCU on

addition affected airplanes. For some

airplanes, it also will require that a

wiring modification be accomplished

prior to replacement of the GCU. The

actions specified by this AD are

intended to prevent such improper

functioning of the GCU, which could

result in the loss of the standby

emergency generation system.

DATES: Effective April 3, 1997.

The incorporation by reference of

certain publications, as listed in the

regulations, is approved by the Director

of the Federal Register as of April 3,

1997.

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)

by superseding AD 91–01–01,

amendment 39–6845 (55 FR 51895,

December 18, 1990), which is applicable

to certain Airbus Model A320–111,

–211, and –231 series airplanes, was

published in the Federal Register on

October 23, 1996 (61 FR 54963). The

action proposed to supersede AD 91–

01–01 to continue to require

replacement of the existing standby

GCU with an improved standby GCU.

The action also proposed to require the

identical replacement to be

accomplished on additional airplanes.

In addition, for some airplanes, the

action proposed that a wiring

modification be accomplished prior to

replacement of the GCU.

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.

Support for the Proposal

Both commenters support the

proposed 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 as proposed.

Cost Impact

There are approximately 106 Airbus

Model A320 series airplanes of U.S.

registry that will be affected by this AD.

Of this number, 18 were previously

subject to the requirements of AD 91–

01–01, and the remaining 88 are the

airplanes that have been added to the

AD applicability by this action.

The replacement of the GCU that is

required by this AD takes approximately

1.5 work hours per airplane to

accomplish, at an average labor rate of

$60 per work hour. Required parts will

cost approximately $450 per airplane.

Based on these figures, the cost impact

of this required action on U.S. operators

is estimated to be $57,240 for the entire

affected fleet (or $540 per airplane).

However, based on the effective date

and the compliance time established by

AD 91–01–01, the FAA assumes that the

18 airplanes that were previously

subject to that AD already have

completed the required replacement of

the GCU. Therefore, the future cost

impact of the replacement action is only

$47,520 (for the 88 airplanes that have

been added to the applicability of the

AD).

For airplanes on which the

modification of the wiring assembly is

required, it will take approximately 8.5

work hours to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of this

action on U.S. operators of those

airplanes is estimated to be $510 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the new 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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–6845 (55 FR

51895, December 18, 1990), and by

adding a new airworthiness directive
Federal Register / Vol. 62, No. 39 / Thursday, February 27, 1997 / Rules and Regulations 8873

(AD), amendment 39–9948, to read as

follows:

97–05–04 Airbus Industrie: Amendment 39–

9948. Docket 96–NM–11–AD.

Supersedes AD 91–01–01, Amendment

39–6845.

Applicability: Model A320 series airplanes;

on which a generator control unit (GCU)

having part number (P/N) 520915 has not

been installed, or on which Airbus

Modification 21052 (reference Airbus Service

Bulletin A320–24–1022) and Airbus

Modification 21736 (reference Airbus Service

Bulletin A320–24–1035) have not been

accomplished; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

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 loss of the standby emergency

generation system, which provides necessary

back-up capability when both main

generators fail, accomplish the following:

Note 2: Airbus Service Bulletin A320–24–

1035 and Airbus Service Bulletin A320–24–

1022 refer to Vickers Service Bulletin No.

520754–24–01 as an additional source of

specific procedural information.

(a) For Model A320–111, –211, and –231

series airplanes; having serial numbers 003

through 058, inclusive, 060 through 067,

inclusive, 069 through 072, inclusive, 074

through 083, inclusive, and 085: Within 150

days after January 28, 1991 (the effective date

of AD 91–01–01, amendment 39–6845),

remove one generator control unit (GCU)

identified as 1XE part number (P/N) 520754,

and install a modified GCU identified as 1XE,

P/N 520915, in accordance with Airbus

Service Bulletin A320–24–1035, Revision 1,

dated February 27, 1990, or Revision 2, dated

June 24, 1994. Following installation,

perform an operational test of the emergency

generation system, emergency GCU from the

centralized fault display system, and the

static inverter, in accordance with the service

bulletin.

(b) For airplanes not subject to paragraph

(a) of this AD: Within 150 days after the

effective date of this AD, accomplish either

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

applicable.

Note 3: Replacement of the GCU

accomplished prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A320–24–1035, Revision 1, dated

February 27, 1990, is considered acceptable

for compliance with the actions specified in

this paragraph.

(1) For airplanes equipped with GCU 1XE

having P/N 520754: Replace the GCU 1XE,

having P/N 520754, in zone 125 of the

avionics compartment, with a modified GCU

1XE, having P/N 520915, in accordance with

Airbus Service Bulletin A320–24–1035,

Revision 2, dated June 24, 1994. Prior to

further flight following accomplishment of

the replacement, perform an operational test

of the affected components in accordance

with that service bulletin.

(2) For airplanes equipped with GCU 1XE

having P/N 520738: Accomplish the

requirements of paragraphs (b)(2)(i) and

(b)(2)(ii) of this AD:

(i) Modify the wiring in relay box 103VU,

the wiring in power center AC/DC emergency

106VU, and the wiring between 103VU and

106VU, in accordance with Airbus Service

Bulletin A320–24–1022, Revision 1, dated

February 27, 1990.

Note 4: Modification accomplished prior to

the effective date of this AD in accordance

with Airbus Service Bulletin A320–24–1022,

dated June 16, 1989, is considered acceptable

for compliance with this paragraph.

(ii) After modifying the wiring, replace the

GCU 1XE, having P/N 520738, located in the

nose gear well in zone 125, with a modified

GCU 1XE, having P/N 520915, in accordance

with Airbus Service Bulletin A320–24–1035,

Revision 2, dated June 24, 1994. Prior to

further flight following accomplishment of

the replacement, perform an operational test

of the affected components in accordance

with that service bulletin.

(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, 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 5: 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) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(e) The actions shall be done in accordance

with the following Airbus Service Bulletins,

which contain the specified lists effective

pages:

Service bulletin number and date Page No. Revision level shown

on page Date shown on page

A320–24–1035, Revision 1, February 27, 1990 .................... 1, 2 ..............................................

3, 4 ..............................................

1 ................................

Original ......................

February 27, 1990.

October 20, 1989.

A320–24–1035, Revision 2, June 24, 1994 ........................... 1–4 .............................................. 2 ................................ June 24, 1994.

A320–24–1022, Revision 1, February 27, 1990 .................... 1, 5, 6, 13, 14, 19–21 .................

2–4, 7–12, 15–18, 22 ..................

1 ................................

Original ......................

February 27, 1990.

June 16, 1989.

The incorporation by reference of the

service documents listed above is

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.

(f) This amendment becomes effective

on April 3, 1997.

Issued in Renton, Washington, on February

20, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–4715 Filed 2–26–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–116–AD; Amendment

39–9949; AD 97–05–05]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires a