Airworthiness Directive 2002-21-10
recurringAirworthiness Directives; Pratt and Whitney PW4000 Series Turbofan Engines
What this AD requires
This amendment supersedes an existing airworthiness directive (AD) that is applicable to Pratt and Whitney (PW) model 4000 series turbofan engines. That action required PW4000 engines with potentially reduced stability margin to be limited to no more than one engine on each airplane, and required removing engines that exceed high pressure compressor (HPC) cycles-since-overhaul (CSO) or cycles-since-new (CSN) from service based on the engine's configuration and category. That action also required establishing a minimum build standard for engines that are returned to service, and performing cool-engine fuel spike testing (Testing-21) on engines to be returned to service after having exceeded HPC cyclic limits or after shop maintenance. This amendment establishes requirements similar to those in the existing AD being superseded, and introduces a rules-based criterion to determine the engine category classification for engines installed on Airbus A300 airplanes. This amendment also adds requirements to manage the engine configurations installed on Boeing 747 airplanes, and requires that repetitive Testing-21 be performed on certain configuration engines. This amendment also establishes criteria that requires Testing-21 on certain engines with Phase 0 or Phase 1, FB2T, or FB2B fan blade configurations. In addition, this amendment re- establishes high pressure compressor (HPC)-to-high pressure-turbine (HPT) cycles-since-overhaul (CSO) cyclic mismatch criteria, and adds criteria to address engine installation changes, engine transfers, and thrust rating changes. Also, this amendment establishes criteria to allow engine stagger without performing Testing-21 for engines which are over their respective limits. This amendment also introduces new requirements on the Phase 3, first run subpopulation engines which were identified after the issuance of NPRM Docket No. 2000-NE-47-AD. The Phase 3, first run subpopulation engines have a significant increase in surge rate and Testing-21 failure rate than the rest of the PW4000 fleet. In order to manage the subpopulation engines to preclude a dual-engine surge, immediate action is required. This immediately adopted rule includes the requirements proposed in the NPRM as well as the required actions for the Phase 3, first run subpopulation engines. This amendment is prompted by investigation and evaluation of PW4000 series turbofan engines surge data, and continuing reports of surges in the PW4000 fleet. The actions specified in this AD are intended to prevent engine takeoff power losses due to HPC surge.
Which aircraft AD 2002-21-10 applies to
AD addresses HPC-surge-related takeoff power loss; applicability depends on engine configuration (Phase 1 without HPT 1st turbine vane cut back = Config A, Phase 1 with 1TVCB = Config B, Phase 3 2nd Run = Config C) determined per Table 1, referencing Pratt & Whitney SB PW4ENG 72-514. Specific PW engine model number not stated in retrieved text.
Whether AD 2002-21-10 actually applies to your aircraft (by serial and installed parts) and whether it’s already complied with comes from that aircraft’s records.
How AD compliance is recorded
A valid compliance record (14 CFR 43.9) states:
Tailplate reads a tail number’s logbooks and matches every applicable AD — including this one — to its compliance evidence, with recurring next-due dates computed.
Look up a tail number →Read the full directive (Federal Register)Applicability is derived from the FAA directive corpus and is advisory, not a legal airworthiness determination. Compliance is established only from an aircraft’s actual records.